advance design - graitecstarting with version 2012, graitec advance has made significant steps...

Advance Design

Validation Guide

INTRODUCTION Before being officially released, each version of GRAITEC software, including Advance Design, undergoes a series of validation tests. This validation is performed in parallel and in addition to manual testing and beta testing, in order to obtain the "operational version" status. This document contains a description of the automatic tests, highlighting the theoretical background and the results we have obtained using the current software release.

Usually, a test is made of a reference (independent from the specific software version tested), a transformation (a calculation or a data processing scenario), a result (given by the specific software version tested) and a difference usually measured in percentage as a drift from a set of reference values. Depending on the cases, the used reference is either a theoretical calculation done manually, a sample taken from the technical literature, or the result of a previous version considered as good by experience.

Starting with version 2012, Graitec Advance has made significant steps forward in term of quality management by extending the scope and automating the testing process. While in previous versions, the tests were always about the calculation results which were compared to a reference set, starting with version 2012, tests have been extended to user interface behavior, import/export procedures, etc. The next major improvement is the capacity to pass the tests automatically. These current tests have obviously been passed on the “operational version”, but they are actually passed on a daily basis during the development process, which helps improve the daily quality by solving potential issues, immediately after they have been introduced in the code.

In the field of structural analysis and design, software users must keep in mind that the results highly depend on the modeling (especially when dealing with finite elements) and on the settings of the numerous assumptions and options available in the software. A software package cannot replace engineers experience and analysis. Despite all our efforts in term of quality management, we cannot guaranty the correct behavior and the validity of the results issued by Advance Design in any situation. With this validation guide, we are providing a set of concrete test cases showing the behavior of Advance Design in various areas and various conditions. The tests cover a wide field of expertise: modeling, climatic load generation according to Eurocode 1, combinations management, meshing, finite element calculation, reinforced concrete design according to Eurocode 2, steel member design according to Eurocode 3, steel connection design according to Eurocode 3, timber member design according to Eurocode 5, seismic analysis according to Eurocode 8, report generation, import / export procedures and user interface behavior.

We hope that this guide will highly contribute to the knowledge and the confidence you are placing in Advance Design.

Manuel LIEDOT

Chief Product Officer

ADVANCE DESIGN VALIDATION GUIDE

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CONTENTS

1 FINITE ELEMENTS ANALYSIS ..............................................................................................................................17 1.1 Cantilever rectangular plate (01-0001SSLSB_FEM)................................................................................18 1.2 System of two bars with three hinges (01-0002SSLLB_FEM) .................................................................20 1.3 Circular plate under uniform load (01-0003SSLSB_FEM)........................................................................23 1.4 Slender beam with variable section (fixed-free) (01-0004SDLLB_FEM)..................................................26 1.5 Tied (sub-tensioned) beam (01-0005SSLLB_FEM) .................................................................................29 1.6 Thin circular ring fixed in two points (01-0006SDLLB_FEM)....................................................................34 1.7 Thin lozenge-shaped plate fixed on one side (alpha = 0 °) (01-0007SDLSB_FEM) ................................38 1.8 Thin lozenge-shaped plate fixed on one side (alpha = 15 °) (01-0008SDLSB_FEM) ..............................41 1.9 Thin lozenge-shaped plate fixed on one side (alpha = 30 °) (01-0009SDLSB_FEM) ..............................44 1.10 Thin lozenge-shaped plate fixed on one side (alpha = 45 °) (01-0010SDLSB_FEM) ..............................47 1.11 Vibration mode of a thin piping elbow in plane (case 1) (01-0011SDLLB_FEM) .....................................50 1.12 Vibration mode of a thin piping elbow in plane (case 2) (01-0012SDLLB_FEM) .....................................53 1.13 Vibration mode of a thin piping elbow in plane (case 3) (01-0013SDLLB_FEM) .....................................56 1.14 Thin circular ring hanged on an elastic element (01-0014SDLLB_FEM) .................................................59 1.15 Double fixed beam with a spring at mid span (01-0015SSLLB_FEM) .....................................................63 1.16 Double fixed beam (01-0016SDLLB_FEM) ..............................................................................................66 1.17 Short beam on simple supports (on the neutral axis) (01-0017SDLLB_FEM) .........................................70 1.18 Short beam on simple supports (eccentric) (01-0018SDLLB_FEM) ........................................................74 1.19 Thin square plate fixed on one side (01-0019SDLSB_FEM)....................................................................78 1.20 Rectangular thin plate simply supported on its perimeter (01-0020SDLSB_FEM) ..................................82 1.21 Cantilever beam in Eulerian buckling (01-0021SFLLB_FEM) ..................................................................86 1.22 Annular thin plate fixed on a hub (repetitive circular structure) (01-0022SDLSB_FEM) ..........................88 1.23 Bending effects of a symmetrical portal frame (01-0023SDLLB_FEM)....................................................90 1.24 Slender beam on two fixed supports (01-0024SSLLB_FEM)...................................................................93 1.25 Slender beam on three supports (01-0025SSLLB_FEM).........................................................................97 1.26 Bimetallic: Fixed beams connected to a stiff element (01-0026SSLLB_FEM) .......................................101 1.27 Fixed thin arc in planar bending (01-0027SSLLB_FEM) ........................................................................104 1.28 Fixed thin arc in out of plane bending (01-0028SSLLB_FEM) ...............................................................107 1.29 Double hinged thin arc in planar bending (01-0029SSLLB_FEM)..........................................................109 1.30 Portal frame with lateral connections (01-0030SSLLB_FEM) ................................................................112 1.31 Truss with hinged bars under a punctual load (01-0031SSLLB_FEM) ..................................................115 1.32 Beam on elastic soil, free ends (01-0032SSLLB_FEM) .........................................................................118 1.33 EDF Pylon (01-0033SFLLA_FEM)..........................................................................................................121 1.34 Beam on elastic soil, hinged ends (01-0034SSLLB_FEM).....................................................................125 1.35 Simply supported square plate (01-0036SSLSB_FEM) .........................................................................129 1.36 Caisson beam in torsion (01-0037SSLSB_FEM) ...................................................................................131


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1.37 Thin cylinder under a uniform radial pressure (01-0038SSLSB_FEM) ..................................................134 1.38 Square plate under planar stresses (01-0039SSLSB_FEM) ..................................................................136 1.39 Stiffen membrane (01-0040SSLSB_FEM)..............................................................................................139 1.40 Beam on two supports considering the shear force (01-0041SSLLB_FEM) ..........................................142 1.41 Thin cylinder under a uniform axial load (01-0042SSLSB_FEM) ...........................................................144 1.42 Thin cylinder under a hydrostatic pressure (01-0043SSLSB_FEM).......................................................147 1.43 Thin cylinder under its self weight (01-0044SSLSB_MEF).....................................................................150 1.44 Torus with uniform internal pressure (01-0045SSLSB_FEM).................................................................152 1.45 Spherical shell under internal pressure (01-0046SSLSB_FEM).............................................................154 1.46 Pinch cylindrical shell (01-0048SSLSB_FEM)........................................................................................157 1.47 Spherical shell with holes (01-0049SSLSB_FEM)..................................................................................159 1.48 Spherical dome under a uniform external pressure (01-0050SSLSB_FEM)..........................................162 1.49 Simply supported square plate under a uniform load (01-0051SSLSB_FEM) .......................................165 1.50 Simply supported rectangular plate under a uniform load (01-0052SSLSB_FEM) ................................167 1.51 Simply supported rectangular plate under a uniform load (01-0053SSLSB_FEM) ................................169 1.52 Simply supported rectangular plate loaded with punctual force and moments (01-0054SSLSB_FEM) ..171 1.53 Shear plate perpendicular to the medium surface (01-0055SSLSB_FEM) ............................................173 1.54 Triangulated system with hinged bars (01-0056SSLLB_FEM)...............................................................175 1.55 A plate (0.01 m thick), fixed on its perimeter, loaded with a uniform pressure (01-0057SSLSB_FEM).177 1.56 A plate (0.01333 m thick), fixed on its perimeter, loaded with a uniform pressure (01-0058SSLSB_FEM)......179 1.57 A plate (0.02 m thick), fixed on its perimeter, loaded with a uniform pressure (01-0059SSLSB_FEM).181 1.58 A plate (0.05 m thick), fixed on its perimeter, loaded with a uniform pressure (01-0060SSLSB_FEM).183 1.59 A plate (0.1 m thick), fixed on its perimeter, loaded with a uniform pressure (01-0061SSLSB_FEM)...185 1.60 A plate (0.01 m thick), fixed on its perimeter, loaded with a punctual force (01-0062SSLSB_FEM) .....187 1.61 A plate (0.01333 m thick), fixed on its perimeter, loaded with a punctual force (01-0063SSLSB_FEM) .........190 1.62 A plate (0.02 m thick), fixed on its perimeter, loaded with a punctual force (01-0064SSLSB_FEM) .....193 1.63 A plate (0.05 m thick), fixed on its perimeter, loaded with a punctual force (01-0065SSLSB_FEM) .....195 1.64 A plate (0.1 m thick), fixed on its perimeter, loaded with a punctual force (01-0066SSLSB_FEM) .......197 1.65 Vibration mode of a thin piping elbow in space (case 1) (01-0067SDLLB_FEM)...................................199 1.66 Vibration mode of a thin piping elbow in space (case 2) (01-0068SDLLB_FEM)...................................201 1.67 Vibration mode of a thin piping elbow in space (case 3) (01-0069SDLLB_FEM)...................................204 1.68 Reactions on supports and bending moments on a 2D portal frame (Rafters) (01-0077SSLPB_FEM) ........207 1.69 Reactions on supports and bending moments on a 2D portal frame (Columns) (01-0078SSLPB_FEM) .......209 1.70 Short beam on two hinged supports (01-0084SSLLB_FEM)..................................................................211 1.71 Slender beam of variable rectangular section with fixed-free ends (ß=5) (01-0085SDLLB_FEM).........213 1.72 Slender beam of variable rectangular section (fixed-fixed) (01-0086SDLLB_FEM)...............................218 1.73 Plane portal frame with hinged supports (01-0089SSLLB_FEM)...........................................................221 1.74 Double fixed beam in Eulerian buckling with a thermal load (01-0091HFLLB_FEM).............................223 1.75 Cantilever beam in Eulerian buckling with thermal load (01-0092HFLLB_FEM)....................................225 1.76 A 3D bar structure with elastic support (01-0094SSLLB_FEM)..............................................................227


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1.77 Fixed/free slender beam with centered mass (01-0095SDLLB_FEM) ...................................................234 1.78 Fixed/free slender beam with eccentric mass or inertia (01-0096SDLLB_FEM)....................................239 1.79 Double cross with hinged ends (01-0097SDLLB_FEM) .........................................................................243 1.80 Simple supported beam in free vibration (01-0098SDLLB_FEM) ..........................................................246 1.81 Membrane with hot point (01-0099HSLSB_FEM) ..................................................................................249 1.82 Beam on 3 supports with T/C (k = 0) (01-0100SSNLB_FEM)................................................................252 1.83 Beam on 3 supports with T/C (k -> infinite) (01-0101SSNLB_FEM) ......................................................255 1.84 Beam on 3 supports with T/C (k = -10000 N/m) (01-0102SSNLB_FEM) ...............................................258 1.85 Linear system of truss beams (01-0103SSLLB_FEM) ...........................................................................261 1.86 Non linear system of truss beams (01-0104SSNLB_FEM) ....................................................................264 1.87 Study of a mast subjected to an earthquake (02-0112SMLLB_P92) .....................................................268 1.88 Linear element in simple bending - without compressed reinforcement (02-0162SSLLB_B91) ............274 1.89 Design of a Steel Structure according to CM66 (03-0206SSLLG_CM66) .............................................278 1.90 Design of a 2D portal frame (03-0207SSLLG_CM66)............................................................................286 1.91 Design of a concrete floor with an opening (03-0208SSLLG_BAEL91).................................................293 1.92 Verifying displacements for liniar element for vertical seism (TTAD #11756) ........................................301 1.93 Generating planar efforts before and after selecting a saved vue (TTAD #11849)................................301 1.94 Verifying constraints for triangular mesh on planar element (TTAD #11447) ........................................301 1.95 Verifying forces for triangular meshing on planar element (TTAD #11723) ...........................................301 1.96 Verifying stresses in beam with "extend into wall" property (TTAD #11680)..........................................302 1.97 Verifying diagrams after changing the view from standard (top, left,...) to user view (TTAD #11854) ...302 1.98 Verifying forces results on concrete linear elements (TTAD #11647) ....................................................302 1.99 Generating results for Torsors NZ/Group (TTAD #11633) .....................................................................302 1.100 Verifying Sxx results on beams (TTAD #11599).....................................................................................303 1.101 Verifying the level mass center (TTAD #11573, TTAD #12315) ............................................................303 1.102 Verifying diagrams for Mf Torsors on divided walls (TTAD #11557) ......................................................303 1.103 Verifying results on puctual supports (TTAD #11489) ............................................................................303 1.104 Generating a report with torsors / level (TTAD #11421).........................................................................304 1.105 Verifying nonlinear analysis results for frames with semi-rigid joints and rigid joints (TTAD #11495) ...304 1.106 Verifying tension/compression supports on nonlinear analysis (TTAD #11518) ....................................304 1.107 Verifying tension/compression supports on nonlinear analysis (TTAD #11518) ....................................304 1.108 Verifying the main axes results on a planar element (TTAD #11725) ....................................................305 1.109 Verifying the display of the forces results on planar supports (TTAD #11728) ......................................305 1.110 Verifying the internal forces results for a simple supported steel beam .................................................305 1.111 Verifying forces on elastic linear support which is defined in a user workplane (TTAD #11929)...........305

2 CAD, RENDERING AND VISUALIZATION...........................................................................................................307 2.1 Verifying hide/show elements command (TTAD #11753) ......................................................................308 2.2 System stability during section cut results verification (TTAD #11752)..................................................308 2.3 Verifying the grid text position (TTAD #11704).......................................................................................308 2.4 Verifying the grid text position (TTAD #11657).......................................................................................308


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2.5 Generating combinations (TTAD #11721) ..............................................................................................308 2.6 Verifying the coordinates system symbol (TTAD #11611)......................................................................309 2.7 Verifying descriptive actors after creating analysis (TTAD #11589).......................................................309 2.8 Creating a circle (TTAD #11525) ............................................................................................................309 2.9 Creating a camera (TTAD #11526).........................................................................................................309 2.10 Verifying the local axes of a section cut (TTAD #11681)........................................................................309 2.11 Verifying the snap points behavior during modeling (TTAD #11458) .....................................................310 2.12 Verifying the representation of elements with HEA cross section (TTAD #11328) ................................310 2.13 Verifying the display of the descriptive model in analysis view (TTAD #11462).....................................310 2.14 Verifying the descriptive model display after post processing results in analysis mode (TTAD #11475).............310 2.15 Verifying holes in horizontal planar elements after changing the level height (TTAD #11490) ..............310 2.16 Verifying the display of elements with compound cross sections (TTAD #11486) .................................311 2.17 Modeling using the tracking snap mode (TTAD #10979) .......................................................................311 2.18 Moving a linear element along with the support (TTAD #12110)............................................................311 2.19 Turning on/off the "ghost" rendering mode (TTAD #11999) ...................................................................311 2.20 Verifying the "ghost display on selection" function for saved views (TTAD #12054)..............................311 2.21 Verifying the "ghost" display after changing the display colors (TTAD #12064).....................................312 2.22 Verifying the fixed load scale function (TTAD #12183)...........................................................................312 2.23 Verifying the steel connections modeling (TTAD #11698)......................................................................312 2.24 Verifying the dividing of planars elements which contain openings (TTAD #12229)..............................312 2.25 Verifying the program behavior when trying to create lintel (TTAD #12062)..........................................312 2.26 Verifying the display of punctual loads after changing the load case number (TTAD #11958)..............313 2.27 Verifying the program behavior when launching the analysis on a model with overlapped loads

(TTAD #11837) .......................................................................................................................................313 2.28 Verifying the display of a beam with haunches (TTAD #12299)............................................................313 2.29 Creating base plate connections for non-vertical columns (TTAD #12170) ...........................................313 2.30 Verifying drawing of joints in y-z plan (TTAD #12453)............................................................................313 2.31 Verifying rotation for steel beam with joint (TTAD #12592) ....................................................................314 2.32 Verifying annotation on selection (TTAD #12700) ..................................................................................314

3 CLIMATIC GENERATOR.......................................................................................................................................315 3.1 EC1 NF: generating wind loads on a 3D portal frame with 2 slopes roof (TTAD #11932) .....................316 3.2 EC1: wind load generation on a simple 3D structure with horizontal roof ..............................................316 3.3 EC1: wind load generation on a high building with horizontal roof .........................................................316 3.4 EC1: wind load generation on a simple 3D portal frame with 2 slopes roof (TTAD #11602) .................316 3.5 EC1: wind load generation on simple 3D portal frame with 4 slopes roof (TTAD #11604) ....................317 3.6 EC1: wind load generation on building with multispan roofs ..................................................................317 3.7 EC1: wind load generation on a signboard.............................................................................................317 3.8 EC1: generating wind loads on an isolated roof with 2 slopes (TTAD #11695) .....................................317 3.9 EC1: generating wind loads on duopitch multispan roofs with pitch < 5 degrees (TTAD #11852).........318 3.10 EC1: generating wind loads on double slope 3D portal frame with a fully opened face (DEV2012 #1.6)...318


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3.11 EC1: generating snow loads on a 2 slopes 3D portal frame with gutter (TTAD #11113).......................318 3.12 EC1: generating snow loads on a 3D portal frame with horizontal roof and gutter (TTAD #11113) ......318 3.13 EC1: snow on a 3D portal frame with horizontal roof and parapet with height reduction (TTAD #11191)...319 3.14 EC1: generating snow loads on a 3D portal frame with a roof which has a small span (< 5m) and a

parapet (TTAD #11735)..........................................................................................................................319 3.15 EC1: generating snow loads on duopitch multispan roofs according to German standards

(DIN EN 1991-1-3/NA) (DEV2012 #3.13)...............................................................................................319 3.16 EC1: generating snow loads on monopitch multispan roofs according to German standards

(DIN EN 1991-1-3/NA) (DEV2012 #3.13)...............................................................................................319 3.17 EC1: generating snow loads on two close roofs with different heights according to German standards

(DIN EN 1991-1-3/NA) (DEV2012 #3.13) ...............................................................................................320 3.18 EC1: generating wind loads on a 55m high structure according to German standards

(DIN EN 1991-1-4/NA) (DEV2012 #3.12)...............................................................................................320 3.19 EC1: generating wind loads on double slope 3D portal frame according to Czech standards

(CSN EN 1991-1-4) (DEV2012 #3.18) ...................................................................................................320 3.20 EC1: generating snow loads on two close roofs with different heights according to Czech standards

(CSN EN 1991-1-3) (DEV2012 #3.18) ...................................................................................................320 3.21 EC1: generating wind loads on a 2 slopes 3D portal frame with 2 fully opened windwalls

(TTAD #11937) .......................................................................................................................................321 3.22 EC1: generating snow loads on a 2 slopes 3D portal frame with roof thickness greater than the parapet

height (TTAD #11943) ............................................................................................................................321 3.23 EC1: verifying the snow loads generated on a monopitch frame (TTAD #11302) .................................321 3.24 EC1: generating wind loads on a 2 slopes 3D portal frame using the Romanian national annex

(TTAD #11687) .......................................................................................................................................321 3.25 EC1: generating wind loads on a 2 slopes 3D portal frame (TTAD #11699) ........................................322 3.26 EC1: generating snow loads on a 2 slopes 3D portal frame using the Romanian national annex

(TTAD #11570) .......................................................................................................................................322 3.27 EC1: generating snow loads on a 2 slopes 3D portal frame using the Romanian national annex

(TTAD #11569) .......................................................................................................................................322 3.28 EC1: generating wind loads on a 2 slopes 3D portal frame (TTAD #11531) .........................................322 3.29 NV2009: generating wind loads and snow loads on a simple structure with planar support

(TTAD #11380) .......................................................................................................................................323 3.30 Generating the description of climatic loads report according to EC1 Romanian standards

(TTAD #11688) .......................................................................................................................................323 3.31 EC1: Verifying the geometry of wind loads on an irregular shed. (TTAD #12233).................................323 3.32 EC1: Verifying the wind loads generated on a building with protruding roof (TTAD #12071, #12278) ..323 3.33 EC1: generating snow loads on a 2 slopes 3D portal frame (NF EN 1991-1-3/NA)

(VT : 3.4 - Snow - Example A)................................................................................................................324 3.34 EC1: generating wind loads on a 2 slopes 3D portal frame (NF EN 1991-1-4/NA)

(VT : 3.1 - Wind - Example A).................................................................................................................324 3.35 EC1: generating wind loads on a 3D portal frame with one slope roof (NF EN 1991-1-4/NA)

(VT : 3.2 - Wind - Example B).................................................................................................................324 3.36 EC1: generating wind loads on a 2 slopes 3D portal frame (NF EN 1991-1-4/NA)

(VT : 3.3 - Wind - Example C).................................................................................................................324 3.37 EC1: generating wind loads on a triangular based lattice structure with composed profiles and automatic

calculation of "n" (NF EN 1991-1-4/NA) (TTAD #12276). ......................................................................325


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3.38 EC1: wind loads on a triangular based lattice structure with composed profiles and user imposed n (NF EN 1991-1-4/NA) (TTAD #12276). ..................................................................................................325

3.39 EC1: generating snow loads on a 3 slopes 3D portal frame with parapets (NF EN 1991-1-3/NA) (TTAD #11111) .......................................................................................................................................325

3.40 EC1: Generating snow loads on a 4 slopes shed with gutters. (TTAD #12528) ....................................325 3.41 EC1: Generating snow loads on a 4 slopes shed with gutters. (TTAD #12528) ....................................326 3.42 EC1: Generating snow loads on a single slope with lateral parapets. (TTAD #12606)..........................326 3.43 EC1: generating wind loads on a sqaure based lattice structure with composed profiles and automatic

calculation of "n" (NF EN 1991-1-4/NA) (TTAD #12744)........................................................................326 3.44 NV2009: Verifying wind and snow reports for a protruding roof (TTAD #11318) ...................................326 3.45 NV2009: Generating wind loads on a 2 slopes 3D portal frame at 15 height. (TTAD #12604)..............326

4 COMBINATIONS....................................................................................................................................................327 4.1 Generating combinations (TTAD #11673) ..............................................................................................328 4.2 Generating combinations for NEWEC8.cbn (TTAD #11431)..................................................................328 4.3 Defining concomitance rules for 2 case families (TTAD #11355)...........................................................328 4.4 Generating load combinations with unfavorable and favorable/unfavorable predominant action

(TTAD #11357) .......................................................................................................................................328 4.5 Generating load combinations after changing the load case number (TTAD #11359) ..........................328 4.6 Generating concomitance matrix after adding a new dead load case (TTAD #11361) ..........................329 4.7 Generating the concomitance matrix after switching back the effect for live load (TTAD #11806) ........329 4.8 Generating a set of combinations with seismic group of loads (TTAD #11889).....................................329 4.9 Generating a set of combinations with Q group of loads (TTAD #11960) ..............................................329 4.10 Generating a set of combinations with different Q "Base" types (TTAD #11806) ..................................330 4.11 Performing the combinations concomitance standard test no.1 (DEV2010#1.7) ...................................331 4.12 Performing the combinations concomitance standard test no.2 (DEV2012 #1.7) ..................................331 4.13 Performing the combinations concomitance standard test no.3 (DEV2012 #1.7) ..................................332 4.14 Performing the combinations concomitance standard test no.4 (DEV2012 #1.7) .................................332 4.15 Performing the combinations concomitance standard test no.5 (DEV2012 #1.7) ..................................333 4.16 Performing the combinations concomitance standard test no.6 (DEV2012 #1.7) ..................................333 4.17 Performing the combinations concomitance standard test no.7 (DEV2012 #1.7) ..................................334 4.18 Performing the combinations concomitance standard test no.8 (DEV2012 #1.7) ..................................334 4.19 Performing the combinations concomitance standard test no.9 (DEV2012 #1.7) ..................................335 4.20 Performing the combinations concomitance standard test no.10 (DEV2012 #1.7) ................................335 4.21 Verifying combinations for CZ localization (TTAD #12542) ....................................................................336 4.22 Verifying the combinations description report (TTAD #11632) ...............................................................336

5 CONCRETE DESIGN.............................................................................................................................................337 5.1 EC2: column design with “Nominal Stiffnes method” square section (TTAD #11625) ...........................338 5.2 Verifying reinforced concrete results on a structure with 375 load cases combinations (TTAD #11683)..338 5.3 EC2 : calculation of a square column in traction (TTAD #11892)...........................................................338 5.4 Verifying Aty and Atz for a fixed concrete beam (TTAD #11812) ...........................................................338 5.5 Verifying the reinforced concrete results on a fixed beam (TTAD #11836)............................................339


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5.6 Verifying the longitudinal reinforcement bars for a filled circular column (TTAD #11678)......................339 5.7 Verifying longitudinal reinforcement for linear element (TTAD #11636).................................................339 5.8 Verifying the longitudinal reinforcement for a fixed linear element (TTAD #11700) ...............................340 5.9 Verifying concrete results for planar elements (TTAD #11583)..............................................................340 5.10 Verifying concrete results for linear element (TTAD #11556).................................................................340 5.11 Verifying reinforcement for concrete column (TTAD #11635) ................................................................340 5.12 Verifying the minimum transverse reinforcement area results for an articulated beam (TTAD #11342) ......341 5.13 Verifying the minimum transverse reinforcement area results for articulated beams (TTAD #11342)...341 5.14 Verifying the longitudinal reinforcement for a horizontal concrete bar with rectangular cross section...341 5.15 EC2: Verifying the minimum reinforcement area for a simply supported beam .....................................342 5.16 EC2: Verifying the longitudinal reinforcement area of a beam under a linear load ................................342 5.17 EC2: Verifying the longitudinal reinforcement area of a beam under a linear load - inclined stress strain

behavior law............................................................................................................................................342 5.18 EC2: Verifying the longitudinal reinforcement area for a beam subjected to point loads.......................342 5.19 EC2: Verifying the longitudinal reinforcement area of a beam uner a linear load - bilinear stress-strain

diagram...................................................................................................................................................343 5.20 Modifying the "Design experts" properties for concrete linear elements (TTAD #12498) ......................343 5.21 EC2: Verifying the transverse reinforcement area for a beam subjected to linear loads .......................343 5.22 EC2: Verifying the longitudinal reinforcement are of a beam under a linear load - horizontal level

behavior law............................................................................................................................................343 6 GENERAL APPLICATION.....................................................................................................................................345

6.1 Verifying geometry properties of elements with compound cross sections (TTAD #11601)..................346 6.2 Verifying material properties for C25/30 (TTAD #11617) .......................................................................346 6.3 Verifying the synthetic table by type of connection (TTAD #11422).......................................................346 6.4 Importing a cross section from the Advance Steel profiles library (TTAD #11487)................................346 6.5 Creating and updating model views and post-processing views (TTAD #11552) ..................................347 6.6 Verifying mesh, CAD and climatic forces - LPM meeting .......................................................................347 6.7 Creating a new Advance Design file using the "New" command from the "Standard" toolbar

(TTAD #12102) .......................................................................................................................................347 6.8 Launching the verification of a model containing steel connections (TTAD #12100).............................347 6.9 Verifying the appearance of the local x orientation legend (TTAD #11737)...........................................348 6.10 Creating system trees using the copy/paste commands (DEV2012 #1.5) .............................................348 6.11 Creating system trees using the copy/paste commands (DEV2012 #1.5) .............................................348 6.12 Verifying the objects rename function (TTAD #12162)...........................................................................348 6.13 Generating liquid pressure on horizontal and vertical surfaces (TTAD #10724)....................................349 6.14 Changing the default material (TTAD #11870) .......................................................................................349 6.15 Verifying 2 joined vertical elements with the clipping option enabled (TTAD #12238)...........................349 6.16 Defining the reinforced concrete design assumptions (TTAD #12354) ..................................................349 6.17 Verifying precision for linear and planar concrete cover (TTAD #12525)...............................................350 6.18 Verifying element creation using commas for coordinates (TTAD #11141) ...........................................350


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7 IMPORT / EXPORT................................................................................................................................................351 7.1 Verifying the export of a linear element to GTC (TTAD #10932, TTAD #11952) ...................................352 7.2 Exporting an Advance Design model to DO4 format (DEV2012 #1.10) .................................................352 7.3 Exporting an analysis model to ADA (through GTC) (DEV2012 #1.3) ...................................................352 7.4 Exporting an analysis model to ADA (through GTC) (DEV2012 #1.3) ...................................................352 7.5 Importing GTC files containing elements with haunches from SuperSTRESS (TTAD #12172) ............352 7.6 Importing GTC files containing elements with circular hollow sections, from SuperSTRESS

(TTAD #12197) .......................................................................................................................................353 7.7 Importing GTC files containing elements with circular hollow sections, from SuperSTRESS

(TTAD #12197) .......................................................................................................................................353 7.8 Verifying the GTC files exchange between Advance Design and SuperSTRESS (DEV2012 #1.9) ......353 7.9 System stability when importing AE files with invalid geometry (TTAD #12232)....................................353 7.10 Verifying the releases option of the planar elements edges after the model was exported and imported

via GTC format (TTAD #12137)..............................................................................................................353 7.11 Verifying the load case properties from models imported as GTC files (TTAD #12306)........................354 7.12 Exporting linear elements to IFC format (TTAD #10561) .......................................................................354 7.13 Importing IFC files containing continuous foundations (TTAD #12410) .................................................354 7.14 Importing GTC files containing "PH.RDC" system (TTAD #12055)........................................................354 7.15 Exporting meshed model to GTC (TTAD #12550)..................................................................................354

8 CONNECTION DESIGN.........................................................................................................................................355 8.1 Creating connections groups (TTAD #11797) ........................................................................................356 8.2 Deleting a welded tube connection - 1 gusset bar (TTAD #12630)........................................................356

9 MESH......................................................................................................................................................................357 9.1 Creating triangular mesh for planar elements (TTAD #11727)...............................................................358 9.2 Verifying mesh points (TTAD #11748)....................................................................................................358 9.3 Verifying the mesh for a model with generalized buckling (TTAD #11519)............................................358

10 REPORTS GENERATOR ......................................................................................................................................359 10.1 Generating the critical magnification factors report (TTAD #11379) ......................................................360 10.2 Modal analysis: eigen modes results for a structure with one level........................................................360 10.3 System stability when the column releases interfere with support restraints (TTAD #10557) ...............360 10.4 Generating a report with modal analysis results (TTAD #10849) ...........................................................360 10.5 Creating the rules table (TTAD #11802) .................................................................................................361 10.6 Creating the steel materials description report (TTAD #11954) .............................................................361 10.7 Verifying the model geometry report (TTAD #12201).............................................................................361 10.8 Verifying the global envelope of linear elements forces result (on each 1/4 of mesh element)

(TTAD #12230) .......................................................................................................................................361 10.9 Verifying the global envelope of linear elements forces result (on all quarters of super element)

(TTAD #12230) .......................................................................................................................................362 10.10 Verifying the global envelope of linear elements forces result (on end points and middle of super

element) (TTAD #12230) ........................................................................................................................362 10.11 Verifying the global envelope of linear elements forces result (on start and end of super element)

(TTAD #12230) .......................................................................................................................................362


15

10.12 Verifying signed concomitant linear elements envelopes on Fx report (TTAD #11517) ........................362 10.13 Verifying the global envelope of linear elements forces result (on the start point of super element)

(TTAD #12230) .......................................................................................................................................363 10.14 Verifying the global envelope of linear elements forces result (on the end point of super element)

(TTAD #12230, #12261) .........................................................................................................................363 10.15 Verifying the global envelope of linear elements displacements (on each 1/4 of mesh element)

(TTAD #12230) .......................................................................................................................................363 10.16 Verifying the global envelope of linear elements displacements (on all quarters of super element)

(TTAD #12230) .......................................................................................................................................363 10.17 Verifying the global envelope of linear elements displacements (on end points and middle of super

element) (TTAD #12230) ........................................................................................................................364 10.18 Verifying the global envelope of linear elements displacements (on start and end of super element)

(TTAD #12230) .......................................................................................................................................364 10.19 Verifying the global envelope of linear elements displacements (on the start point of super element)

(TTAD #12230) .......................................................................................................................................364 10.20 Verifying the global envelope of linear elements displacements (on the end point of super element)

(TTAD #12230, TTAD #12261) ..............................................................................................................364 10.21 Verifying the global envelope of linear elements stresses (on each 1/4 of mesh element)

(TTAD #12230) .......................................................................................................................................365 10.22 Verifying the global envelope of linear elements stresses (on all quarters of super element) (TTAD

#12230)...................................................................................................................................................365 10.23 Verifying the global envelope of linear elements stresses (on end points and middle of super element)

(TTAD #12230) .......................................................................................................................................365 10.24 Verifying the global envelope of linear elements stresses (on start and end of super element)

(TTAD #12230) .......................................................................................................................................365 10.25 Verifying the global envelope of linear elements stresses (on the start point of super element)

(TTAD #12230) .......................................................................................................................................366 10.26 Verifying the global envelope of linear elements stresses (on the end point of super element)

(TTAD #12230, TTAD #12261) ..............................................................................................................366 10.27 Verifying the Min/Max values from the user reports (TTAD# 12231) .....................................................366 10.28 Verifying the shape sheet for a steel beam (TTAD #12455) ..................................................................366 10.29 Verifying the EC2 calculation assumptions report (TTAD #11838) ........................................................366 10.30 Verifying the shape sheet report (TTAD #12353) ...................................................................................367 10.31 Verifying the Max row on the user table report (TTAD #12512) .............................................................367 10.32 Verifying the shape sheet strigs display (TTAD #12622) .......................................................................367 10.33 Verifying the steel shape sheet display (TTAD #12657) ........................................................................367 10.34 Verifying report for modal analysis (TTAD #12718)................................................................................367

11 SEISMIC ANALYSIS..............................................................................................................................................369 11.1 EC8 : Verifying the displacements results of a liniar element according to Czech seismic standards

(CSN EN 1998-1) (DEV2012 #3.18).......................................................................................................370 11.2 Verifying the spectrum results for EC8 seism (TTAD #11478)...............................................................370 11.3 Verifying the spectrum results for EC8 seism (TTAD #12472)...............................................................370

12 STEEL DESIGN .....................................................................................................................................................371 12.1 Verifying results on square hollowed beam 275H according to thickness (TTAD #11770)....................372 12.2 Verifying shape sheet on S275 beam (TTAD #11731) ...........................................................................372


16

12.3 Verifying the calculation results for steel cables (TTAD #11623) ...........................................................372 12.4 Generating the shape sheet by system (TTAD #11471) ........................................................................372 12.5 Verifying the shape sheet results for the elements of a simple vault (TTAD #11522)............................373 12.6 Verifying the cross section optimization according to EC3 (TTAD #11516) ...........................................373 12.7 Verifying the shape sheet results for a column (TTAD #11550) .............................................................373 12.8 Verifying the shape sheet results for a fixed horizontal beam (TTAD #11545) ......................................373 12.9 CM66: Verifying the buckling length for a steel portal frame, using the kA kB method..........................374 12.10 CM66: Verifying the buckling length for a steel portal frame, using the roA roB method .......................374 12.11 EC3: Verifying the buckling length for a steel portal frame, using the kA kB method.............................374 12.12 Verifying the steel shape optimization when using sections from Advance Steel Profiles database

(TTAD #11873) .......................................................................................................................................374 12.13 Verifying the buckling coefficient Xy on a class 2 section.......................................................................375 12.14 EC3: Verifying the buckling length results (TTAD #11550) ....................................................................375 12.15 EC3 fire verification: Verifying the work ratios after performing an optimization for steel profiles

(TTAD #11975) .......................................................................................................................................375 12.16 Verifying the "Shape sheet" command for elements which were excluded from the specialized

calculation (TTAD #12389) .....................................................................................................................375 12.17 Changing the steel design template for a linear element (TTAD #12491)..............................................376 12.18 Verifying the shape sheet for a steel beam with circular cross-section (TTAD #12533) ........................376

13 TIMBER DESIGN ...................................................................................................................................................377 13.1 Modifying the "Design experts" properties for timber linear elements (TTAD #12259) ..........................378 13.2 Verifying the timber elements shape sheet (TTAD #12337)...................................................................378 13.3 Verifying the units display in the timber shape sheet (TTAD #12445)....................................................378

14 XML TEMPLATE FILES.........................................................................................................................................379 14.1 Saving the properties of a linear element as a template (DEV2012 #1.4)..............................................380 14.2 Saving the properties of a planar element as a template (DEV2012 #1.4) ............................................380 14.3 Loading a template with the properties of a linear element (DEV2012 #1.4) .........................................380 14.4 Loading a template with the properties of a planar element (DEV2012 #1.4) ........................................380

1 Finite Elements Analysis


18

1.1 Cantilever rectangular plate (01-0001SSLSB_FEM)

Test ID: 2433

Test status: Passed

1.1.1 Description Verifies the vertical displacement on the free extremity of a cantilever rectangular plate fixed on one side. The plate is 1 m long, subjected to a uniform planar load.

1.1.2 Background

1.1.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 01/89. ■ Analysis type: linear static. ■ Element type: planar.

Cantilever rectangular plate Scale =1/4 01-0001SSLSB_FEM

Units

S.I.

Geometry

■ Thickness: e = 0.005 m, ■ Length: l = 1 m, ■ Width: b = 0.1 m.

Materials properties

■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa, ■ Poisson's ratio: ν = 0.3.


19

Boundary conditions

■ Outer: Fixed at end x = 0, ■ Inner: None.

Loadings

■ External: Uniform load p = -1700 Pa on the upper surface, ■ Internal: None.

1.1.2.2 Displacement of the model in the linear elastic range

Reference solution

The reference displacement is calculated for the unsupported end located at x = 1m.

u = bl4p8EIz =

0.1 x 14 x 1700

8 x 2.1 x 1011 x 0.1 x 0.0053

12 = -9.71 cm

Finite elements modeling

■ Planar element: plate, imposed mesh, ■ 1100 nodes, ■ 990 surface quadrangles.

Deformed shape

Deformed cantilever rectangular plate Scale =1/4 01-0001SSLSB_FEM

1.1.2.3 Theoretical results

Solver Result name Result description Reference value CM2 DZ Vertical displacement on the free extremity [cm] -9.71

1.1.3 Calculated results

Result name Result description Value Error DZ Vertical displacement on the free extremity [cm] -9.58696 cm 1.28%


20

1.2 System of two bars with three hinges (01-0002SSLLB_FEM)

Test ID: 2434

Test status: Passed

1.2.1 Description On a system of two bars (AC and BC) with three hinges, a punctual load in applied in point C. The vertical displacement in point C and the tensile stress on the bars are verified.

1.2.2 Background

1.2.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLL 09/89; ■ Analysis type: linear static; ■ Element type: linear.

System of two bars with three hinges Scale =1/33 0002SSLLB_FEM

4.500 m

30° 30°

4.500 m

AA BB

CC

FF

X

Y

Z X

Y

Z

Units

I. S.

Geometry

■ Bars angle relative to horizontal: θ = 30°, ■ Bars length: l = 4.5 m, ■ Bar section: A = 3 x 10-4 m2.


■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa.


21

Boundary conditions

■ Outer: Hinged in A and B, ■ Inner: Hinge on C

Loading

■ External: Punctual load in C: F = -21 x 103 N. ■ Internal: None.

1.2.2.2 Displacement of the model in C

Reference solution

uc = -3 x 10-3 m


■ Linear element: beam, imposed mesh, ■ 21 nodes, ■ 20 linear elements.

Displacement shape

System of two bars with three hinges Scale =1/33 Displacement in C 0002SSLLB_FEM

1.2.2.3 Bars stresses

Reference solutions

σAC bar = 70 MPa

σBC bar = 70 MPa


■ Linear element: beam, imposed mesh, ■ 21 nodes, ■ 20 linear elements.


22

1.2.2.4 Shape of the stress diagram

System of two bars with three hinges Scale =1/34 Bars stresses 0002SSLLB_FEM


Solver Result name Result description Reference value CM2 DZ Vertical displacement in point C [cm] -0.30 CM2 Sxx Tensile stress on AC bar [MPa] 70 CM2 Sxx Tensile stress on BC bar [MPa] 70


Result name Result description Value Error DZ Vertical displacement in point C [cm] -0.299954 cm 0.02% Sxx Tensile stress on AC bar [MPa] 69.9998 MPa 0.00% Sxx Tensile stress on BC bar [MPa] 69.9998 MPa 0.00%


23

1.3 Circular plate under uniform load (01-0003SSLSB_FEM)

Test ID: 2435

Test status: Passed

1.3.1 Description On a circular plate of 5 mm thickness and 2 m diameter, an uniform load, perpendicular on the plan of the plate, is applied. The vertical displacement on the plate center is verified.

1.3.2 Background

1.3.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 03/89; ■ Analysis type: linear static; ■ Element type: planar.

Circular plate under uniform load Scale =1/10 01-0003SSLSB_FEM

Units

I. S.

Geometry

■ Circular plate radius: r = 1m, ■ Circular plate thickness: h = 0.005 m.




24

Boundary conditions

■ Outer: Plate fixed on the side (in all points of its perimeter), For the modeling, we consider only a quarter of the plate and we impose symmetry conditions on some nodes (see the following model; yz plane symmetry condition):translation restrained nodes along x and rotation restrained nodes along y and z: translation restrained nodes along x and rotation restrained nodes along y and z:

■ Inner: None.

Loading

■ External: Uniform loads perpendicular on the plate: pZ = -1000 Pa, ■ Internal: None.

1.3.2.2 Vertical displacement of the model at the center of the plate

Reference solution

Circular plates form:

u = pr4

64D = -1000 x 14

64 x 2404 = - 6.50 x 10-3 m

with the plate radius coefficient: D = Eh3

12(1-ν2) = 2.1 x 1011 x 0.0053

12(1-0.32)

D = 2404


■ Planar element: plate, imposed mesh, ■ 70 nodes, ■ 58 planar elements.

Circular plate under uniform load Scale =1.5 Meshing 01-0003SSLSB_FEM


25

Deformed shape

Circular plate under uniform load Scale =1.5 Deformed 01-0003SSLSB_FEM


Solver Result name Result description Reference value CM2 DZ Vertical displacement on the plate center [mm] -6.50


Result name Result description Value Error DZ Vertical displacement on the plate center [mm] -6.47032 mm 0.46%


26

1.4 Slender beam with variable section (fixed-free) (01-0004SDLLB_FEM)

Test ID: 2436

Test status: Passed

1.4.1 Description Verifies the first eigen mode frequencies for a slender beam with variable section, subjected to its own weight.

1.4.2 Background

1.4.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 09/89; ■ Analysis type: modal analysis; ■ Element type: linear.

Slender beam with variable section (fixed-free) Scale =1/4 01-0004SDLLB_FEM

Units

I. S.

Geometry

■ Beam length: l = 1 m, ■ Initial section (in A):

► Height: h1 = 0.04 m, ► Width: b1 = 0.04 m, ► Section: A1 = 1.6 x 10-3 m2, ► Flexure moment of inertia relative to z-axis: Iz1 = 2.1333 x 10-7 m4,

■ Final section (in B): ► Height: h2 = 0.01 m, ► Width: b2 = 0.01 m, ► Section: A2 = 10-4 m2, ► Flexure moment of inertia relative to z-axis: Iz2 = 8.3333 x 10-10 m4.


27


■ Longitudinal elastic modulus: E = 2 x 1011 Pa, ■ Density: 7800 kg/m3.

Boundary conditions

■ Outer: Fixed in A, ■ Inner: None.

Loading

■ External: None, ■ Internal: None.

1.4.2.2 Eigen mode frequencies

Reference solutions

Precise calculation by numerical integration of the differential equation of beams bending (Euler-Bernoulli theories):

∂2

∂x2 (EIz ∂2v∂x2 ) = -ρA

∂2v∂x2 where Iz and A vary with the abscissa.

The result is: fi = 12π λi

h2l2

E12ρ

λ1 λ2 λ3 λ4 λ5 23.289 73.9 165.23 299.7 478.1


■ Linear element: variable beam, imposed mesh, ■ 31 nodes, ■ 30 linear elements.

Eigen mode shapes


28


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 frequency [Hz] 54.18 CM2 Eigen mode Eigen mode 2 frequency [Hz] 171.94 CM2 Eigen mode Eigen mode 3 frequency [Hz] 384.4 CM2 Eigen mode Eigen mode 4 frequency [Hz] 697.24 CM2 Eigen mode Eigen mode 5 frequency [Hz] 1112.28


Result name Result description Value Error Eigen mode 1 frequency [Hz] 54.01 Hz -0.31% Eigen mode 2 frequency [Hz] 170.58 Hz -0.80% Eigen mode 3 frequency [Hz] 378.87 Hz -1.46% Eigen mode 4 frequency [Hz] 681.31 Hz -2.34% Eigen mode 5 frequency [Hz] 1075.7 Hz -3.40%


29

1.5 Tied (sub-tensioned) beam (01-0005SSLLB_FEM)

Test ID: 2437

Test status: Passed

1.5.1 Description Verifies the tension force on a beam reinforced by a system of hinged bars, subjected to a uniform linear load.

1.5.2 Background

1.5.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLL 13/89; ■ Analysis type: static, thermoelastic (plane problem); ■ Element type: linear.

Tied (sub-tensioned) beam Scale =1/37 01-0005SSLLB_FEM

Units

I. S.

Geometry

■ Length: ► AD = FB = a = 2 m, ► DF = CE = b = 4 m, ► CD = EF = c = 0.6 m, ► AC = EB = d = 2.088 m, ► Total length: L = 8 m,

■ AD, DF, FB Beams: ► Section: A = 0.01516 m2, ► Shear area: Ar = A / 2.5, ► Inertia moment: I = 2.174 x 10-4 m4,


30

■ CE Bar: ► Section: A1 = 4.5 x 10-3 m2,

■ AC, EB bar: ► Section: A2 = 4.5 x 10-3 m2,

■ CD, EF bars: ► Section: A3 = 3.48 x 10-3 m2.


■ Isotropic linear elastic material, ■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa, ■ Shearing module: G = 0.4x E.

Boundary conditions

■ Outer: Hinged in A, support connection in B (blocked vertical translation), ■ Inner: Hinged at bar ends: AC, CD, EF, EB.

Loading

■ External: Uniform linear load p = -50000 N/ml, ■ Internal: Shortening of the CE tie of δ = 6.52 x 10-3 m (dilatation coefficient: αCE = 1 x 10-5 /°C and temperature

variation ΔT = -163°C).

1.5.2.2 Compression force in CE bar

Reference solution

The solution is established by considering the deformation effects due to the shear force and normal force:

μ = 1 - 43 x

aL

k = AAr

= 2.5

t = IA

γ = (L/c)2 x (1+ (A/A1) x (b/L) + 2 x (A/A2) x (d/a)2 x (d/L) + 2 x (A/A3) (c/a)2 x (c/L)

τ = k x [(2Et2) / (GaL)]

ρ = μ + γ + τ

μ0 = 1 – (a/L)2 x (2 – a/L)

τ0 = 6k x (E/G) x (t/L)2 x (1 + b/L)

ρ0 = μ0 + τ0

NCE = - (1/12) x (pL2/c) x (ρ0 /ρ) + (EI/(Lc2)) x (δ/ρ) = 584584 N


Linear element: without meshing,

■ AD, DF, FB: S beam (considering the shear force deformations), ■ AC, CD, EF, EB: bar, ■ CE: beam, ■ 6 nodes.


31

Force diagrams

Tied (sub-tensioned) beam Scale =1/31 Compression force in CE bar

1.5.2.3 Bending moment at point H

Reference solution

MH = - (1/8) x pL2 x [1- (2/3) x (ρ0/ρ)] – (EI/(Lc)) x (δ/p) = 49249.5 N


Linear element: without meshing,

■ AD, DF, FB: S beam (considering the shear force deformations), ■ AC, CD, EF, EB: bar, ■ CE: beam, ■ 6 nodes.


32

Shape of the bending moment diagram

Tied (sub-tensioned) beam Scale =1/31 Mz bending moment

1.5.2.4 Vertical displacement at point D

Reference solution

The reference displacement vD provided by AFNOR is determined by averaging the results of several software with implemented finite elements method.

vD = -0.5428 x 10-3 m


■ Linear element: without meshing, ► AD, DF, FB: S beam (considering the shear force deformations), ► AC, CD, EF, EB: bar, ► CE: beam,

■ 6 nodes.


33

Deformed shape

Tied (sub-tensioned) beam Scale =1/31 Deformed


Solver Result name Result description Reference value CM2 FX Tension force on CE bar [N] 584584


Result name Result description Value Error Fx Tension force on CE bar [N] 584580 N 0.00%


34

1.6 Thin circular ring fixed in two points (01-0006SDLLB_FEM)

Test ID: 2438

Test status: Passed

1.6.1 Description Verifies the first eigen modes frequencies for a thin circular ring fixed in two points, subjected to its own weight only.

1.6.2 Background

1.6.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 12/89; ■ Analysis type: modal analysis, plane problem; ■ Element type: linear.

Thin circular ring fixed in two points Scale =1/2 01-0006SDLLB_FEM

Units

I. S.

Geometry

■ Average radius of curvature: OA = OB = R = 0.1 m, ■ Angular spacing between points A and B: 120° ; ■ Rectangular straight section:

► Thickness: h = 0.005 m, ► Width: b = 0.010 m, ► Section: A = 5 x 10-5 m2, ► Flexure moment of inertia relative to the vertical axis: I = 1.042 x 10-10 m4,


35

■ Point coordinates: ► O (0 ;0),

► A (-0.05 3 ; -0.05),

► B (0.05 3 ; -0.05).


■ Longitudinal elastic modulus: E = 7.2 x 1010 Pa ■ Poisson's ratio: ν = 0.3, ■ Density: ρ = 2700 kg/m3.

Boundary conditions

■ Outer: Fixed at A and B, ■ Inner: None.

Loading



Reference solutions

The deformation of the fixed ring is calculated from the deformations of the free-free thin ring

■ Symmetrical mode: ► u’i = i cos(iθ) ► v’i = sin (iθ)

► θ’i = 1-i2R sin (iθ)

■ Antisymmetrical mode: ► u’i = i sin(iθ) ► v’i = -cos (iθ)

► θ’i = 1-i2R cos (iθ)

From Green’s method results:

fj = π21

λj ⋅2R

h 12E

ρ with a support angle of 120°.

i 1 2 3 4 Symmetrical mode 4.8497 14.7614 23.6157

Antisymmetrical mode 1.9832 9.3204 11.8490 21.5545


■ Linear element: beam, without meshing, ■ 32 nodes, ■ 32 linear elements.


36

Eigen mode shapes


37

1.6.2.3 Theoretic results

Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 frequency - 1 antisymmetric 1 [Hz] 235.3 CM2 Eigen mode Eigen mode 2 frequency - 2 symmetric 1 [Hz] 575.3 CM2 Eigen mode Eigen mode 3 frequency - 3 antisymmetric 2 [Hz] 1105.7 CM2 Eigen mode Eigen mode 4 frequency - 4 antisymmetric 3 [Hz] 1405.6 CM2 Eigen mode Eigen mode 5 frequency - 5 symmetric 2 [Hz] 1751.1 CM2 Eigen mode Eigen mode 6 frequency - 6 antisymmetric 4 [Hz] 2557 CM2 Eigen mode Eigen mode 7 frequency - 7 symmetric 3 [Hz] 2801.5


Result name Result description Value Error Eigen mode 1 frequency - 1 antisymmetric 1 [Hz] 236.32 Hz 0.43% Eigen mode 2 frequency - 2 symmetric 1 [Hz] 578.52 Hz 0.56% Eigen mode 3 frequency - 3 antisymmetric 2 [Hz] 1112.54 Hz 0.61% Eigen mode 4 frequency - 4 antisymmetric 3 [Hz] 1414.22 Hz 0.61% Eigen mode 5 frequency - 5 symmetric 2 [Hz] 1760 Hz 0.51% Eigen mode 6 frequency - 6 antisymmetric 4 [Hz] 2569.97 Hz 0.50% Eigen mode 7 frequency - 7 symmetric 3 [Hz] 2777.43 Hz -0.87%


38

1.7 Thin lozenge-shaped plate fixed on one side (alpha = 0 °) (01-0007SDLSB_FEM)

Test ID: 2439

Test status: Passed

1.7.1 Description Verifies the eigen modes frequencies for a 10 mm thick lozenge-shaped plate fixed on one side, subjected to its own weight only.

1.7.2 Background

1.7.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLS 02/89; ■ Analysis type: modal analysis; ■ Element type: planar.

Thin lozenge-shaped plate fixed on one side Scale =1/10 01-0007SDLSB_FEM

Units

I. S.

Geometry

■ Thickness: t = 0.01 m, ■ Side: a = 1 m, ■ α = 0° ■ Points coordinates:

► A ( 0 ; 0 ; 0 ) ► B ( a ; 0 ; 0 ) ► C ( 0 ; a ; 0 ) ► D ( a ; a ; 0 )


39


■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa, ■ Poisson's ratio: ν = 0.3, ■ Density: ρ = 7800 kg/m3.

Boundary conditions

■ Outer: AB side fixed, ■ Inner: None.

Loading


1.7.2.2 Eigen mode frequencies relative to the α angle

Reference solution

M. V. Barton formula for a side "a" lozenge, leads to the frequencies:

fj = ⋅⋅π 2a21

λi2

)1(12Et

2

2

ν−ρ where i = 1,2, and λi

2 = g(α).

α = 0 λ1

2 3.492 λ2

2 8.525

M.V. Barton noted the sensitivity of the result relative to the mode and the α angle. He acknowledged that the λi values were determined with a limited development of an insufficient order, which led to consider a reference value that is based on an experimental result, verified by an average of seven software that use the finite elements calculation method.



Eigen mode shapes


40


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 frequency [Hz] 8.7266 CM2 Eigen mode Eigen mode 2 frequency [Hz] 21.3042


Result name Result description Value Error Eigen mode 1 frequency [Hz] 8.67 Hz -0.65% Eigen mode 2 frequency [Hz] 21.21 Hz -0.44%


41


Test ID: 2440

Test status: Passed


1.8.2 Background



Units

I. S.

Geometry


► A ( 0 ; 0 ; 0 ) ► B ( a ; 0 ; 0 ) ► C ( 0.259a ; 0.966a ; 0 ) ► D ( 1.259a ; 0.966a ; 0 )


42



Boundary conditions


Loading


1.8.2.2 Eigen modes frequencies function by α angle

Reference solution

M. V. Barton formula for a lozenge of side "a" leads to the frequencies:

fj = ⋅⋅π 2a21

λi2

)1(12Et

2

2

ν−ρ where i = 1,2, or λi

2 = g(α).

α = 15° λ1

2 3.601 λ2

2 8.872 M. V. Barton noted the sensitivity of the result relative to the mode and the α angle. He acknowledged that the λi values were determined with a limited development of an insufficient order, which led to consider a reference value that is based on an experimental result, verified by an average of seven software that use the finite elements calculation method.



Eigen mode shapes


43






44


Test ID: 2441

Test status: Passed


1.9.2 Background



Units

I. S.

Geometry


► A ( 0 ; 0 ; 0 ) ► B ( a ; 0 ; 0 )

► C ( 0.5a ; 3 2 a ; 0 )

► D ( 1.5a ; 3 2 a ; 0 )


45



Boundary conditions


Loading



Reference solution


fj = ⋅⋅π 2a21

λi2

)1(12Et

2

2


2 = g(α).

α = 30° λ1

2 3.961 λ2

2 10.19

M. V. Barton noted the sensitivity of the result relative to the mode and the α angle. He acknowledged that the λi values were determined with a limited development of an insufficient order, which led to consider a reference value that is based on an experimental result, verified by an average of seven software that use the finite elements calculation method.



Eigen mode shapes


46






47


Test ID: 2442

Test status: Passed


1.10.2 Background



Units

I. S.

Geometry


► A ( 0 ; 0 ; 0 ) ► B ( a ; 0 ; 0 )

► C ( 22

a ; 22

a ; 0 )

► D (2

22 +a ;

22

a ; 0 )


48



Boundary conditions


Loading



Reference solution


fj = ⋅⋅π 2a21

λi2

)1(12Et

2

2


2 = g(α).

α = 45° λ1

2 4.4502 λ2

2 10.56

M. V. Barton noted the sensitivity of the result relative to the mode and the α angle. He acknowledged that the λi values were determined with a limited development of an insufficient order, which led to consider a reference value that is based on an experimental result, verified by an average of seven software that use the finite elements calculation method.



Eigen mode shapes


49




Result name Result description Value Error Eigen mode 1 frequency [Hz] 11.28 Hz 1.41% Eigen mode 2 frequency [Hz] 28.08 Hz 6.02%


50

1.11 Vibration mode of a thin piping elbow in plane (case 1) (01-0011SDLLB_FEM)

Test ID: 2443

Test status: Passed

1.11.1 Description Verifies the vibration modes of a thin piping elbow (1 m radius) with fixed ends and subjected to its self weight only.

1.11.2 Background

1.11.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 14/89; ■ Analysis type: modal analysis (plane problem); ■ Element type: linear.

Vibration mode of a thin piping elbow in plane Scale = 1/7 Case 1 01-0011SDLLB_FEM

Units

I. S.

Geometry

■ Average radius of curvature: OA = R = 1 m, ■ Straight circular hollow section: ■ Outer diameter: de = 0.020 m, ■ Inner diameter: di = 0.016 m, ■ Section: A = 1.131 x 10-4 m2, ■ Flexure moment of inertia relative to the y-axis: Iy = 4.637 x 10-9 m4, ■ Flexure moment of inertia relative to z-axis: Iz = 4.637 x 10-9 m4, ■ Polar inertia: Ip = 9.274 x 10-9 m4.


51

■ Points coordinates (in m): ► O ( 0 ; 0 ; 0 ) ► A ( 0 ; R ; 0 ) ► B ( R ; 0 ; 0 )



Boundary conditions

■ Outer: Fixed at points A and B , ■ Inner: None.

Loading



Reference solution

The Rayleigh method applied to a thin curved beam is used to determine parameters such as:

■ in plane bending:

fj = 2

2i

R2 ⋅π

λ

AEIz

ρ where i = 1,2,


■ Linear element: beam, ■ 11 nodes, ■ 10 linear elements.

Eigen mode shapes


52


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode frequency in plane 1 [Hz] 119 CM2 Eigen mode Eigen mode frequency in plane 2 [Hz] 227


Result name Result description Value Error Eigen mode frequency in plane 1 [Hz] 120.09 Hz 0.91% Eigen mode frequency in plane 2 [Hz] 227.1 Hz 0.04%


53


Test ID: 2444

Test status: Passed

1.12.1 Description Verifies the vibration modes of a thin piping elbow (1 m radius) extended by two straight elements of length L, subjected to its self weight only.

1.12.2 Background


Vibration mode of a thin piping elbow Scale = 1/11 Case 2 01-0012SDLLB_FEM

Units

I. S.

Geometry

■ Average radius of curvature: OA = R = 1 m, ■ L = 0.6 m, ■ Straight circular hollow section: ■ Outer diameter de = 0.020 m, ■ Inner diameter di = 0.016 m, ■ Section: A = 1.131 x 10-4 m2, ■ Flexure moment of inertia relative to the y-axis: Iy = 4.637 x 10-9 m4, ■ Flexure moment of inertia relative to z-axis: Iz = 4.637 x 10-9 m4, ■ Polar inertia: Ip = 9.274 x 10-9 m4.


54

■ Points coordinates (in m): ► O ( 0 ; 0 ; 0 ) ► A ( 0 ; R ; 0 ) ► B ( R ; 0 ; 0 ) ► C ( -L ; R ; 0 ) ► D ( R ; -L ; 0 )



Boundary conditions

■ Outer: ► Fixed at points C and D ► At A: translation restraint along y and z, ► At B: translation restraint along x and z,

■ Inner: None.

Loading



Reference solution



fj = 2

2i

R2 ⋅π

λ

AEIz

ρ where i = 1,2,




55

Eigen mode shapes


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode frequency in plane 1 [Hz] 94 CM2 Eigen mode Eigen mode frequency in plane 2 [Hz] 180


Result name Result description Value Error Eigen mode frequency in plane 1 [Hz] 94.62 Hz 0.66% Eigen mode frequency in plane 2 [Hz] 184.68 Hz 2.53%


56


Test ID: 2445

Test status: Passed

1.13.1 Description Verifies the vibration modes of a thin piping elbow (1 m radius) extended by two straight elements of length L, subjected to its self weight only.

1.13.2 Background


Vibration mode of a thin piping elbow Scale = 1/12 Case 3 01-0013SDLLB_FEM

Units

I. S.

Geometry



57




Boundary conditions

■ Outer: ► Fixed at points C and Ds, ► At A: translation restraint along y and z, ► At B: translation restraint along x and z,

■ Inner: None.

Loading



Reference solution



fj = 2

2i

R2 ⋅π

λ

AEIz

ρ where i = 1,2,




58

Eigen mode shapes


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode frequency in plane 1 [Hz] 25.300 CM2 Eigen mode Eigen mode frequency in plane 2 [Hz] 27.000


Result name Result description Value Error Eigen mode frequency in plane 1 [Hz] 24.96 Hz -1.36% Eigen mode frequency in plane 2 [Hz] 26.71 Hz -1.09%


59

1.14 Thin circular ring hanged on an elastic element (01-0014SDLLB_FEM)

Test ID: 2446

Test status: Passed

1.14.1 Description Verifies the first eigen modes frequencies of a circular ring hanged on an elastic element, subjected to its self weight only.

1.14.2 Background

1.14.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 13/89; ■ Analysis type: modal analysis, plane problem; ■ Element type: linear.

Thin circular ring hang from an elastic element Scale = 1/1 01-0014SDLLB_FEM

Units

I. S.

Geometry

■ Average radius of curvature: OB = R = 0.1 m, ■ Length of elastic element: AB = 0.0275 m ;


60

■ Straight rectangular section: ► Ring

Thickness: h = 0.005 m,

Width: b = 0.010 m,

Section: A = 5 x 10-5 m2,

Flexure moment of relative to the vertical axis: I = 1.042 x 10-10 m4,

► Elastic element Thickness: h = 0.003 m,

Width: b = 0.010 m,

Section: A = 3 x 10-5 m2,

Flexure moment of inertia relative to the vertical axis: I = 2.25 x 10-11 m4,

■ Points coordinates: ► O ( 0 ; 0 ), ► A ( 0 ; -0.0725 ), ► B ( 0 ; -0.1 ).



Boundary conditions

■ Outer: Fixed in A, ■ Inner: None.

Loading



Reference solutions

The reference solution was established from experimental results of a mass manufactured aluminum ring.




61

Eigen mode shapes


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 Asymmetrical frequency [Hz] 28.80 CM2 Eigen mode Eigen mode 2 Symmetrical frequency [Hz] 189.30 CM2 Eigen mode Eigen mode 3 Asymmetrical frequency [Hz] 268.80 CM2 Eigen mode Eigen mode 4 Asymmetrical frequency [Hz] 641.00 CM2 Eigen mode Eigen mode 5 Symmetrical frequency [Hz] 682.00 CM2 Eigen mode Eigen mode 6 Asymmetrical frequency [Hz] 1063.00


62


Result name Result description Value Error Eigen mode 1 Asymmetrical frequency [Hz] 28.81 Hz 0.03% Eigen mode 2 Symmetrical frequency [Hz] 189.69 Hz 0.21% Eigen mode 3 Asymmetrical frequency [Hz] 269.38 Hz 0.22% Eigen mode 4 Asymmetrical frequency [Hz] 642.15 Hz 0.18% Eigen mode 5 Symmetrical frequency [Hz] 683.9 Hz 0.28% Eigen mode 6 Asymmetrical frequency [Hz] 1065.73 Hz 0.26%


63

1.15 Double fixed beam with a spring at mid span (01-0015SSLLB_FEM)

Test ID: 2447

Test status: Passed

1.15.1 Description Verifies the vertical displacement on the middle of a beam consisting of four elements of length "l", having identical characteristics. A punctual load of -10000 N is applied.

1.15.2 Background

1.15.2.1 Model description ■ Reference: internal GRAITEC test; ■ Analysis type: linear static; ■ Element type: linear.

Units

I. S.

Geometry

■ l = 1 m ■ S = 0.01 m2 ■ I = 0.0001 m4



Boundary conditions

■ Outer: ■ Fixed at ends x = 0 and x = 4 m, ■ Elastic support with k = EI/l rigidity ■ Inner: None.

Loading

■ External: Punctual load P = -10000 N at x = 2m, ■ Internal: None.


64


Reference solution

The reference vertical displacement v3, is calculated at the middle of the beam at x = 2 m.

Rigidity matrix of a plane beam:

[ ]

⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢

⎣

⎡

−

−−−

−

−

−

=

llll

llll

ll

lll

llll

ll

EIEIEIEI

EIEIEIEI

EIEIEIEI

EIEIEIEI

460260

61206120

00l

ES00ES

260460

61206120

00ES-00ES

K

22

2323

22

2323

e

Given the symmetry / X and load of the structure, it is unnecessary to consider the degrees of freedom associated with normal work (u2, u3, u4).

The same symmetry allows the deduction of:

■ v2 = v4 ■ β2 = -β4 ■ β3 = 0

( )( )( )( )( )( )654321

000

00

4626

612612

268026

612024612

268026

6120124612

268026

612024612

2646

612612

5

5

1

1

5

5

4

4

3

3

2

2

1

1

22

22

22

22

22

22

22

22

22

22

⎪⎪⎪⎪⎪⎪⎪

⎭

⎪⎪⎪⎪⎪⎪⎪

⎬

⎫

⎪⎪⎪⎪⎪⎪⎪

⎩

⎪⎪⎪⎪⎪⎪⎪

⎨

⎧

−=

⎪⎪⎪⎪⎪⎪⎪

⎭

⎪⎪⎪⎪⎪⎪⎪

⎬

⎫

⎪⎪⎪⎪⎪⎪⎪

⎩

⎪⎪⎪⎪⎪⎪⎪

⎨

⎧

⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢

⎣

⎡

−

−−−

−

−−−

−

−⎟⎠

⎞⎜⎝

⎛ +−−

−

−−−

−

−

MR

P

MR

v

v

v

v

v

EI

β

β

β

β

β

llll

llll

lllll

lllll

lllll

llllll

lllll

lllll

llll

llll

33

333

333

333

33


65

The elementary rigidity matrix of the spring in its local axis system, [ ])()(

1111

6

35 U

UEIk ⎥⎦

⎤⎢⎣

⎡−

−=

l, must be expressed in

the global axis system by means of the rotation matrix (90° rotation):

[ ]

( )( )( )( )( )( )6

6

6

3

3

3

5

000000010010000000000000010010000000

β

β

vu

vu

EIK

⎥⎥⎥⎥⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢⎢⎢⎢⎢

⎣

⎡

−

−

=l

→ 344332 43 0826 vvllll

−=⇒=++ βββ

→ 344332332 024612 vvvv =⇒=+−−

lllβ

→ y)unnecessar(usually 026826244423222 vvvv =⇒=+−++ βββ

lllll

(3) → ( ) m 10 11905.03

612124612 032

3

34243332223−−=

+−=⇒−=−−⎟

⎠

⎞⎜⎝

⎛ ++−−EIl

PvEIPvvv

llllllββ


■ Linear element: beam, imposed mesh, ■ 6 nodes, ■ 4 linear elements + 1 spring,

Deformed shape

Double fixed beam with a spring at mid span Deformed

Note: the displacement is expressed here in μm


Solver Result name Result description Reference value CM2 Dz Vertical displacement on the middle of the beam [mm] -0.11905


Result name Result description Value Error Dz Vertical displacement on the middle of the beam [mm] -0.119048 mm 0.00%


66

1.16 Double fixed beam (01-0016SDLLB_FEM)

Test ID: 2448

Test status: Passed

1.16.1 Description Verifies the eigen modes frequencies and the vertical displacement on the middle of a beam consisting of eight elements of length "l", having identical characteristics. A punctual load of -50000 N is applied.

1.16.2 Background

1.16.2.1 Model description ■ Reference: internal GRAITEC test (beams theory); ■ Analysis type: static linear, modal analysis; ■ Element type: linear.

Units

I. S.

Geometry

■ Length: l = 16 m, ■ Axial section: S=0.06 m2 ■ Inertia I = 0.0001 m4


■ Longitudinal elastic modulus: E = 2.1 x 1011 N/m2, ■ Poisson's ratio: ν = 0.3, ■ Density: ρ = 7850 kg/m3

Boundary conditions

■ Outer: Fixed at both ends x = 0 and x = 8 m, ■ Inner: None.

Loading

■ External: Punctual load P = -50000 N at x = 4m, ■ Internal: None.


67


Reference solution

The reference vertical displacement v5, is calculated at the middle of the beam at x = 2 m.

m 05079.00001.0111.2192

1650000192

33

5 =××

×==

EEIPlv


■ Linear element: beam, imposed mesh, ■ 9 nodes, ■ 8 elements.

Deformed shape

Double fixed beam Deformed

1.16.2.3 Eigen mode frequencies of the model in the linear elastic range

Reference solution

Knowing that the first four eigen mode frequencies of a double fixed beam are given by the following formula:

SIE

Lf nn .

...2 2

2

ρπχ

= where for the first 4 eigen modes frequencies

⎪⎪

⎩

⎪⎪

⎨

⎧

→=

→=

→=

→=

Hz 26.228=f 8.199

Hz 15.871=f 9.120

Hz 8.095=f 67.61

Hz 2.937=f 37.22

424

323

222

121

χ

χ

χ

χ




68

Modal deformations

Double fixed beam Mode 1





69


Solver Result name Result description Reference value CM2 Dz Vertical displacement on the middle of the beam [m] -0.05079 CM2 Eigen mode Eigen mode 1 frequency [Hz] 2.937 CM2 Eigen mode Eigen mode 2 frequency [Hz] 8.095 CM2 Eigen mode Eigen mode 3 frequency [Hz] 15.870 CM2 Eigen mode Eigen mode 4 frequency [Hz] 26.228


Result name Result description Value Error Dz Vertical displacement on the middle of the beam [m] -0.0507937 m -0.01% Eigen mode 1 frequency [Hz] 2.94 Hz 0.10% Eigen mode 2 frequency [Hz] 8.09 Hz -0.06% Eigen mode 3 frequency [Hz] 15.79 Hz -0.51% Eigen mode 4 frequency [Hz] 25.76 Hz -1.82%


70

1.17 Short beam on simple supports (on the neutral axis) (01-0017SDLLB_FEM)

Test ID: 2449

Test status: Passed

1.17.1 Description Verifies the first eigen mode frequencies of a short beam on simple supports (the supports are located on the neutral axis), subjected to its own weight only.

1.17.2 Background ■ Reference: Structure Calculation Software Validation Guide, test SDLL 01/89; ■ Analysis type: modal analysis (plane problem); ■ Element type: linear.

Short beam on simple supports on the neutral axis Scale = 1/6 01-0017SDLLB_FEM

Units

I. S.

Geometry

■ Height: h = 0.2 m, ■ Length: l = 1 m, ■ Width: b = 0.1 m, ■ Section: A = 2 x 10-2 m4, ■ Flexure moment of inertia relative to z-axis: Iz = 6.667 x 10-5 m4.




71

Boundary conditions

■ Outer: ► Hinged at A (null horizontal and vertical displacements), ► Simple support in B.

■ Inner: None.

Loading

■ External: None. ■ Internal: None.

1.17.2.1 Eigen modes frequencies

Reference solution

The bending beams equation gives, when superimposing, the effects of simple bending, shear force deformations and rotation inertia, Timoshenko formula.

The reference eigen modes frequencies are determined by a numerical simulation of this equation, independent of any software.

The eigen frequencies in tension-compression are given by:

fi = ⋅π

λl2

i ρE

where λi = 2

)1i2( −


■ Linear element: S beam, imposed mesh, ■ 10 nodes, ■ 9 linear elements.


72

Eigen mode shapes


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 frequency [Hz] 431.555 CM2 Eigen mode Eigen mode 2 frequency [Hz] 1265.924 CM2 Eigen mode Eigen mode 3 frequency [Hz] 1498.295 CM2 Eigen mode Eigen mode 4 frequency [Hz] 2870.661 CM2 Eigen mode Eigen mode 5 frequency [Hz] 3797.773 CM2 Eigen mode Eigen mode 6 frequency [Hz] 4377.837


73


Result name Result description Value Error Eigen mode 1 frequency [Hz] 437.12 Hz 1.27% Eigen mode 2 frequency [Hz] 1264.32 Hz -0.13% Eigen mode 3 frequency [Hz] 1537.16 Hz 2.53% Eigen mode 4 frequency [Hz] 2911.46 Hz 1.40% Eigen mode 5 frequency [Hz] 3754.54 Hz -1.15% Eigen mode 6 frequency [Hz] 4281.23 Hz -2.26%


74

1.18 Short beam on simple supports (eccentric) (01-0018SDLLB_FEM)

Test ID: 2450

Test status: Passed

1.18.1 Description Verifies the first eigen mode frequencies of a short beam on simple supports (the supports are eccentric relative to the neutral axis).

1.18.2 Background

1.18.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 01/89; ■ Analysis type: modal analysis, (plane problem); ■ Element type: linear.

Short beam on simple supports (eccentric) Scale = 1/5 01-0018SDLLB_FEM

Units

I. S.

Geometry

■ Height: h = 0.2m, ■ Length: l = 1 m, ■ Width: b = 0.1 m, ■ Section: A = 2 x 10-2 m4, ■ Flexure moment of inertia relative to z-axis: Iz = 6.667 x 10-5 m4.


75



Boundary conditions

■ Outer: ► Hinged at A (null horizontal and vertical displacements), ► Simple support at B.

■ Inner: None.

Loading



Reference solution

The problem has no analytical solution, the solution is determined by averaging several software: Timoshenko model with shear force deformation effects and rotation inertia. The bending modes and the traction-compression are coupled.


■ Linear element: S beam, imposed mesh, ■ 10 nodes, ■ 9 linear elements.

Eigen modes shape

Short beam on simple supports (eccentric) Mode 1


76





77



Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 frequency [Hz] 392.8 CM2 Eigen mode Eigen mode 2 frequency [Hz] 902.2 CM2 Eigen mode Eigen mode 3 frequency [Hz] 1591.9 CM2 Eigen mode Eigen mode 4 frequency [Hz] 2629.2 CM2 Eigen mode Eigen mode 5 frequency [Hz] 3126.2


Result name Result description Value Error Eigen mode 1 frequency [Hz] 393.7 Hz 0.23% Eigen mode 2 frequency [Hz] 945.35 Hz 4.56% Eigen mode 3 frequency [Hz] 1595.94 Hz 0.25% Eigen mode 4 frequency [Hz] 2526.22 Hz -4.08% Eigen mode 5 frequency [Hz] 3118.91 Hz -0.23%


78

1.19 Thin square plate fixed on one side (01-0019SDLSB_FEM)

Test ID: 2451

Test status: Passed

1.19.1 Description Verifies the first eigen modes frequencies of a thin square plate fixed on one side.

1.19.2 Background


Thin square plate fixed on one side Scale = 1/6 01-0019SDLSB_FEM

Units

I. S.

Geometry

■ Side: a = 1 m, ■ Thickness: t = 1 m, ■ Points coordinates in m:

► A (0 ;0 ;0) ► B (1 ;0 ;0) ► C (1 ;1 ;0) ► D (0 ;1 ;0)


79



Boundary conditions

■ Outer: Edge AD fixed. ■ Inner: None.

Loading



Reference solution

M. V. Barton formula for a square plate with side "a", leads to:

fj = 2a2

1⋅π

λi2

)1(12Et

2

2

ν−ρ where i = 1,2, . . .

i 1 2 3 4 5 6 λi 3.492 8.525 21.43 27.33 31.11 54.44


■ Planar element: shell, ■ 959 nodes, ■ 900 planar elements.


80

Eigen mode shapes

Thin square plate fixed on one side Mode 1




81


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 frequency [Hz] 8.7266 CM2 Eigen mode Eigen mode 2 frequency [Hz] 21.3042 CM2 Eigen mode Eigen mode 3 frequency [Hz] 53.5542 CM2 Eigen mode Eigen mode 4 frequency [Hz] 68.2984 CM2 Eigen mode Eigen mode 5 frequency [Hz] 77.7448 CM2 Eigen mode Eigen mode 6 frequency [Hz] 136.0471


Result name Result description Value Error Eigen mode 1 frequency [Hz] 8.67 Hz -0.65% Eigen mode 2 frequency [Hz] 21.22 Hz -0.40% Eigen mode 3 frequency [Hz] 53.13 Hz -0.80% Eigen mode 4 frequency [Hz] 67.74 Hz -0.82% Eigen mode 5 frequency [Hz] 77.15 Hz -0.77% Eigen mode 6 frequency [Hz] 134.65 Hz -1.04%


82

1.20 Rectangular thin plate simply supported on its perimeter (01-0020SDLSB_FEM)

Test ID: 2452

Test status: Passed

1.20.1 Description Verifies the first eigen mode frequencies of a thin rectangular plate fixed simply supported on its perimeter.

1.20.2 Background


Rectangular thin plate simply supported on its perimeter Scale = 1/8 01-0020SDLSB_FEM

Units

I. S.

Geometry

■ Length: a = 1.5 m, ■ Width: b = 1 m, ■ Thickness: t = 0.01 m, ■ Points coordinates in m:

► A (0 ;0 ;0) ► B (0 ;1.5 ;0) ► C (1 ;1.5 ;0) ► D (1 ;0 ;0)


83



Boundary conditions

■ Outer: ► Simple support on all sides, ► For the modeling: hinged at A, B and D.

■ Inner: None.

Loading



Reference solution

M. V. Barton formula for a rectangular plate with supports on all four sides, leads to:

fij = 2π

[ ( ai

)2 + ( bj

)2] )1(12

Et2

2

ν−ρ

where:

i = number of half-length of wave along y ( dimension a)

j = number of half-length of wave along x ( dimension b)




84

Eigen mode shapes


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 1; j = 1. [Hz] 35.63 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 2; j = 1. [Hz] 68.51 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 1; j = 2. [Hz] 109.62 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 3; j = 1. [Hz] 123.32 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 2; j = 2. [Hz] 142.51 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 3; j = 2. [Hz] 197.32


85


Result name Result description Value Error Eigen mode "i" - "j" frequency, for i = 1; j = 1 (Mode 1) [Hz] 35.58 Hz -0.14% Eigen mode "i" - "j" frequency, for i = 2; j = 1 (Mode 2) [Hz] 68.29 Hz -0.32% Eigen mode "i" - "j" frequency, for i = 1; j = 2 (Mode 3) [Hz] 109.98 Hz 0.33% Eigen mode "i" - "j" frequency, for i = 3; j = 1 (Mode 4) [Hz] 123.02 Hz -0.24% Eigen mode "i" - "j" frequency, for i = 2; j = 2 (Mode 5) [Hz] 141.98 Hz -0.37% Eigen mode "i" - "j" frequency, for i = 3; j = 2 (Mode 6) [Hz] 195.55 Hz -0.91%


86

1.21 Cantilever beam in Eulerian buckling (01-0021SFLLB_FEM)

Test ID: 2453

Test status: Passed

1.21.1 Description Verifies the critical load result on node 5 of a cantilever beam in Eulerian buckling. A punctual load of -100000 is applied.

1.21.2 Background

1.21.2.1 Model description ■ Reference: internal GRAITEC test (Euler theory); ■ Analysis type: Eulerian buckling; ■ Element type: linear.

Units

I. S.

Geometry

■ L = 10 m ■ S=0.01 m2 ■ I = 0.0002 m4


■ Longitudinal elastic modulus: E = 2.0 x 1010 N/m2, ■ Poisson's ratio: ν = 0.1.

Boundary conditions


Loading

■ External: Punctual load P = -100000 N at x = L, ■ Internal: None.


87

1.21.2.2 Critical load on node 5

Reference solution

The reference critical load established by Euler is:

98696.010000098696N 98696

L4EIP 2

2

critique ==λ⇒=π

=


■ Planar element: beam, imposed mesh, ■ 5 nodes, ■ 4 elements.

Deformed shape


Solver Result name Result description Reference value CM2 Fx Critical load on node 5. [N] -98696


Result name Result description Value Error Fx Critical load on node 5 (mode 1) [N] -100000 N -1.30%


88

1.22 Annular thin plate fixed on a hub (repetitive circular structure) (01-0022SDLSB_FEM)

Test ID: 2454

Test status: Passed

1.22.1 Description Verifies the eigen mode frequencies of a thin annular plate fixed on a hub.

1.22.2 Background

1.22.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLS 04/89; ■ Analysis type: modal analysis; ■ Element type: planar element.

Annular thin plate fixed on a hub (repetitive circular structure) Scale = 1/3 01-0022SDLSB_FEM

Units

I. S.

Geometry

■ Inner radius: Ri = 0.1 m, ■ Outer radius: Re = 0.2 m, ■ Thickness: t = 0.001 m.

Material properties



89

Boundary conditions

■ Outer: Fixed on a hub at any point r = Ri. ■ Inner: None.

Loading



Reference solution

The solution of determining the frequency based on Bessel functions leads to the following formula:

fij = 1

2πRe2 λij

2 Et2

12ρ(1-ν2)

where:

i = the number of nodal diameters

j = the number of nodal circles

and λij2 such as:

j \ i 0 1 2 3 0 13.0 13.3 14.7 18.5 1 85.1 86.7 91.7 100


■ Planar element: plate, ■ 360 nodes, ■ 288 planar elements.


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 0; j = 0. [Hz] 79.26 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 0; j = 1. [Hz] 518.85 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 1; j = 0. [Hz] 81.09 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 1; j = 1. [Hz] 528.61 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 2; j = 0. [Hz] 89.63 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 2; j = 1. [Hz] 559.09 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 3; j = 0. [Hz] 112.79 CM2 Eigen mode Eigen mode “i" - “j” frequency, for i = 3; j = 1. [Hz] 609.70


Result name Result description Value Error Eigen mode "i" - "j" frequency, for i = 0; j = 0 (Mode 1) [Hz] 79.05 Hz -0.27% Eigen mode "i" - "j" frequency, for i = 0; j = 1 (Mode 18) [Hz] 521.84 Hz 0.57% Eigen mode "i" - "j" frequency, for i = 1; j = 0 (Mode 2) [Hz] 80.52 Hz -0.71% Eigen mode "i" - "j" frequency, for i = 1; j = 1 (Mode 20) [Hz] 529.49 Hz 0.17% Eigen mode "i" - "j" frequency, for i = 2; j = 0 (Mode 4) [Hz] 88.43 Hz -1.36% Eigen mode “i" - “j” frequency, for i = 2; j = 1 (Mode 22) [Hz] 552.43 Hz -1.21% Eigen mode "i" - "j" frequency, for i = 3; j = 0 (Mode 7) [Hz] 110.27 Hz -2.29% Eigen mode "i" - "j" frequency, for i = 3; j = 1 (Mode 25) [Hz] 593.83 Hz -2.67%


90

1.23 Bending effects of a symmetrical portal frame (01-0023SDLLB_FEM)

Test ID: 2455

Test status: Passed

1.23.1 Description Verifies the first eigen mode frequencies of a symmetrical portal frame with fixed supports.

1.23.2 Background

1.23.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 01/89; ■ Analysis type: modal analysis; ■ Element type: linear.

Bending effects of a symmetrical portal frame Scale = 1/5 01-0023SDLLB_FEM

Units

I. S.

Geometry

■ Straight rectangular sections for beams and columns: ■ Thickness: h = 0.0048 m, ■ Width: b = 0.029 m, ■ Section: A = 1.392 x 10-4 m2, ■ Flexure moment of inertia relative to z-axis: Iz = 2.673 x 10-10 m4, ■ Points coordinates in m:

A B C D E F x -0.30 0.30 -0.30 0.30 -0.30 0.30 y 0 0 0.36 0.36 0.81 0.81


91



Boundary conditions


Loading



Reference solution

Dynamic radius method (slender beams theory).



Deformed shape

Bending effects of a symmetrical portal frame Scale = 1/7 Mode 13


92


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode 1 antisymmetric frequency [Hz] 8.8 CM2 Eigen mode Eigen mode 2 antisymmetric frequency [Hz] 29.4 CM2 Eigen mode Eigen mode 3 symmetric frequency [Hz] 43.8 CM2 Eigen mode Eigen mode 4 symmetric frequency [Hz] 56.3 CM2 Eigen mode Eigen mode 5 antisymmetric frequency [Hz] 96.2 CM2 Eigen mode Eigen mode 6 symmetric frequency [Hz] 102.6 CM2 Eigen mode Eigen mode 7 antisymmetric frequency [Hz] 147.1 CM2 Eigen mode Eigen mode 8 symmetric frequency [Hz] 174.8 CM2 Eigen mode Eigen mode 9 antisymmetric frequency [Hz] 178.8 CM2 Eigen mode Eigen mode 10 antisymmetric frequency [Hz] 206 CM2 Eigen mode Eigen mode 11 symmetric frequency [Hz] 266.4 CM2 Eigen mode Eigen mode 12 antisymmetric frequency [Hz] 320 CM2 Eigen mode Eigen mode 13 symmetric frequency [Hz] 335


Result name Result description Value Error Eigen mode 1 antisymmetric frequency [Hz] 8.78 Hz -0.23% Eigen mode 2 antisymmetric frequency [Hz] 29.43 Hz 0.10% Eigen mode 3 symmetric frequency [Hz] 43.85 Hz 0.11% Eigen mode 4 symmetric frequency [Hz] 56.3 Hz 0.00% Eigen mode 5 antisymmetric frequency [Hz] 96.05 Hz -0.16% Eigen mode 6 symmetric frequency [Hz] 102.7 Hz 0.10% Eigen mode 7 antisymmetric frequency [Hz] 147.08 Hz -0.01% Eigen mode 8 symmetric frequency [Hz] 174.96 Hz 0.09% Eigen mode 9 antisymmetric frequency [Hz] 178.92 Hz 0.07% Eigen mode 10 antisymmetric frequency [Hz] 206.23 Hz 0.11% Eigen mode 11 symmetric frequency [Hz] 266.62 Hz 0.08% Eigen mode 12 antisymmetric frequency [Hz] 319.95 Hz -0.02% Eigen mode 13 symmetric frequency [Hz] 334.96 Hz -0.01%


93

1.24 Slender beam on two fixed supports (01-0024SSLLB_FEM)

Test ID: 2456

Test status: Passed

1.24.1 Description A straight slender beam with fixed ends is loaded with a uniform load, several punctual loads and a torque. The shear force, bending moment, vertical displacement and horizontal reaction are verified.

1.24.2 Background


Slender beam on two fixed supports Scale = 1/4 01-0024SSLLB_FEM

Units

I. S.

Geometry

■ Length: L = 1 m, ■ Beam inertia: I = 1.7 x 10-8 m4.


■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa.

Boundary conditions



94

Loading

■ External: ► Uniformly distributed load from A to B: py = p = -24000 N/m, ► Punctual load at D: Fx = F1 = 30000 N, ► Torque at D: Cz = C = -3000 Nm, ► Punctual load at E: Fx = F2 = 10000 N, ► Punctual load at E: Fy = F = -20000 N.

■ Internal: None.

1.24.2.2 Shear force at G

Reference solution

Analytical solution:

■ Shear force at G: VG

VG = 0.216F – 1.26 LC



Results shape

Slender beam on two fixed supports Scale = 1/5 Shear force


95

1.24.2.3 Bending moment in G

Reference solution


■ Bending moment at G: MG

MG = pL2

24 - 0.045LF – 0.3C



Results shape

Slender beam on two fixed supports Scale = 1/5 Bending moment

1.24.2.4 Vertical displacement at G

Reference solution


■ Vertical displacement at G: vG

vG = pl4

384EI + 0.003375FL3

EI + 0.015CL2

EI




96

Results shape

Slender beam on two fixed supports Scale = 1/4 Deformed

1.24.2.5 Horizontal reaction at A

Reference solution


■ Horizontal reaction at A: HA HA = -0.7F1 –0.3F2




Solver Result name Result description Reference value CM2 Fz Shear force in point G. [N] -540 CM2 My Bending moment in point G. [Nm] -2800 CM2 Dz Vertical displacement in point G. [cm] -4.90 CM2 Fx Horizontal reaction in point A. [N] 24000

Calculated results

Result name Result description Value Error Fz Shear force in point G [N] -540 N 0.00% My Bending moment in point G [Nm] -2800 N*m 0.00% DZ Vertical displacement in point G [cm] -4.90485 cm -0.10% Fx Horizontal reaction in point A [N] 24000 N 0.00%


97

1.25 Slender beam on three supports (01-0025SSLLB_FEM)

Test ID: 2457

Test status: Passed

1.25.1 Description A straight slender beam on three supports is loaded with two punctual loads. The bending moment, vertical displacement and reaction on the center are verified.

1.25.2 Background

1.25.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLL 03/89; ■ Analysis type: static (plane problem); ■ Element type: linear.

Slender beam on three supports Scale = 1/49 01-0025SSLLB_FEM

Units

I. S.

Geometry

■ Length: L = 3 m, ■ Beam inertia: I = 6.3 x 10-4 m4.


98


Longitudinal elastic modulus: E = 2.1 x 1011 Pa.

Boundary conditions

■ Outer: ► Hinged at A, ► Elastic support at B (Ky = 2.1 x 106 N/m), ► Simple support at C.

■ Inner: None.

Loading

■ External: 2 punctual loads F = Fy = -42000N. ■ Internal: None.

1.25.2.2 Bending moment at B

Reference solution

The resolution of the hyperstatic system of the slender beam leads to:

k = Ky3LEI6

■ Bending moment at B: MB

MB = ± 2L

)k8(F)k26(

++−



Results shape

Slender beam on three supports Scale = 1/49 Bending moment


99

1.25.2.3 Reaction in B

Reference solution

■ Compression force in the spring: VB

VB = -11F8 + k



1.25.2.4 Vertical displacement at B

Reference solution

■ Deflection at the spring location: vB

vB = 11F

Ky(8 + k)



Results shape

Slender beam on three supports Deformed


Solver Result name Result description Reference value CM2 My Bending moment in point B. [Nm] -63000 CM2 DZ Vertical displacement in point B. [cm] -1.00 CM2 Fz Reaction in point B. [N] -21000


100


Result name Result description Value Error My Bending moment in point B [Nm] -63000 N*m 0.00% DZ Vertical displacement in point B [cm] -1 cm 0.00% Fz Reaction in point B [N] -21000 N 0.00%


101

1.26 Bimetallic: Fixed beams connected to a stiff element (01-0026SSLLB_FEM)

Test ID: 2458

Test status: Passed

1.26.1 Description Two beams fixed at one end and rigidly connected to an undeformable beam is loaded with a punctual load. The deflection, vertical reaction and bending moment are verified in several points.

1.26.2 Background


Fixed beams connected to a stiff element Scale = 1/10 01-0026SSLLB_FEM

Units

I. S.

Geometry

■ Lengths: ► L = 2 m, ► l = 0.2 m,

■ Beams inertia moment: I = (4/3) x 10-8 m4, ■ The beam sections are squared, of side: 2 x 10-2 m.


■ Longitudinal elastic modulus: E = 2 x 1011 Pa.


102

Boundary conditions

■ Outer: Fixed in A and C, ■ Inner: The tangents to the deflection of beams AB and CD at B and D remain horizontal; practically, we

restraint translations along x and z at nodes B and D.

Loading

■ External: In D: punctual load F = Fy = -1000N. ■ Internal: None.

1.26.2.2 Deflection at B and D

Reference solution

The theory of slender beams bending (Euler-Bernouilli formula) leads to a deflection at B and D:

The resolution of the hyperstatic system of the slender beam leads to:

vB = vD = FL3

24EI



Results shape

Fixed beams connected to a stiff element Scale = 1/10 Deformed

1.26.2.3 Vertical reaction at A and C

Reference solution

Analytical solution.




103

1.26.2.4 Bending moment at A and C

Reference solution



■ Linear element: beam, ■ 4 nodes, ■ 3 linear elements


Solver Result name Result description Reference value CM2 D Deflection in point B [m] 0.125 CM2 D Deflection in point D [m] 0.125 CM2 Fz Vertical reaction in point A [N] -500 CM2 Fz Vertical reaction in point C [N] -500 CM2 My Bending moment in point A [Nm] 500 CM2 My Bending moment in point C [Nm] 500


Result name Result description Value Error D Deflection in point B [m] 0.125376 m 0.30% D Deflection in point D [m] 0.125376 m 0.30% Fz Vertical reaction in point A [N] -500 N 0.00% Fz Vertical reaction in point C [N] -500 N 0.00% My Bending moment in point A [Nm] 500.083 N*m 0.02% My Bending moment in point C [Nm] 500.083 N*m 0.02%


104

1.27 Fixed thin arc in planar bending (01-0027SSLLB_FEM)

Test ID: 2459

Test status: Passed

1.27.1 Description Arc of a circle fixed at one end, subjected to two punctual loads and a torque at its free end. The horizontal displacement, vertical displacement and rotation about Z-axis are verified.

1.27.2 Background

1.27.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLL 06/89; ■ Analysis type: static linear (plane problem); ■ Element type: linear.

Fixed thin arc in planar bending Scale = 1/24 01-0027SSLLB_FEM

Units

I. S.

Geometry

■ Medium radius: R = 3 m , ■ Circular hollow section:

► de = 0.02 m, ► di = 0.016 m, ► A = 1.131 x 10-4 m2, ► Ix = 4.637 x 10-9 m4.


105


Longitudinal elastic modulus: E = 2 x 1011 Pa.

Boundary conditions

■ Outer: Fixed in A. ■ Inner: None.

Loading

■ External: At B:

► punctual load F1 = Fx = 10 N, ► punctual load F2 = Fy = 5 N, ► bending moment about Oz, Mz = 8 Nm.

■ Internal: None.

1.27.2.2 Displacements at B

Reference solution

At point B:

■ displacement parallel to Ox: u = R2

4EI [F1πR + 2F2R + 4Mz]

■ displacement parallel to Oy: v = R2

4EI [2F1πR + (3π - 8)F2R + 2(π - 2)Mz]

■ rotation around Oz: θ = R

4EI [4F1R + 2(π - 2)F2R + 2πMz]




106

Results shape

Fixed thin arc in planar bending Scale = 1/19 Deformed


Solver Result name Result description Reference value CM2 DX Horizontal displacement in point B [m] 0.3791 CM2 DZ Vertical displacement in point B [m] 0.2417 CM2 RY Rotation about Z-axis in point B [rad] -0.1654


Result name Result description Value Error DX Horizontal displacement in point B [m] 0.378914 m -0.05% DZ Vertical displacement in point B [m] 0.241738 m 0.02% RY Rotation about Z-axis in point B [rad] -0.165362

Rad 0.02%


107

1.28 Fixed thin arc in out of plane bending (01-0028SSLLB_FEM)

Test ID: 2460

Test status: Passed

1.28.1 Description An arc of a circle fixed at one end is loaded with a punctual force at its free end, perpendicular to the plane. The out of plane displacement, torsion moment and bending moment are verified.

1.28.2 Background

1.28.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLL 07/89; ■ Analysis type: static linear; ■ Element type: linear.

Fixed thin arc in out of plane bending Scale = 1/6 01-0028SSLLB_FEM

Units

I. S.

Geometry


► de = 0.02 m, ► di = 0.016 m, ► A = 1.131 x 10-4 m2, ► Ix = 4.637 x 10-9 m4.


108


■ Longitudinal elastic modulus: E = 2 x 1011 Pa, ■ Poisson's ratio: ν = 0.3.

Boundary conditions

■ Outer: Fixed at A. ■ Inner: None.

Loading

■ External: Punctual force in B perpendicular on the plane: Fz = F = 100 N. ■ Internal: None.

1.28.2.2 Displacements at B

Reference solution

Displacement out of plane at point B:

uB = FR3

EIx [ π4 +

EIx KT

(3π4 - 2)]

where KT is the torsional rigidity for a circular section (torsion constant is 2Ix).

KT = 2GIx = EIx

1 + ν ⇒ uB = FR3

EIx [ π4 + (1 + ν) (

3π4 - 2)]



1.28.2.3 Moments at θ = 15°

Reference solution

■ Torsion moment: Mx’ = Mt = FR(1 - sinθ) ■ Bending moment: Mz’ = Mf = -FRcosθ




Solver Result name Result description Reference value CM2 D Displacement out of plane in point B [m] 0.13462 CM2 Mx Torsion moment in θ = 15° [Nm] 74.1180 CM2 Mz Bending moment in θ = 15° [Nm] -96.5925


Result name Result description Value Error D Displacement out of plane in point B [m] 0.135156 m 0.40% Mx Torsion moment in Theta = 15° [Nm] 74.103 N*m -0.02% Mz Bending moment in Theta = 15° [Nm] -96.5925 N*m 0.00%


109

1.29 Double hinged thin arc in planar bending (01-0029SSLLB_FEM)

Test ID: 2461

Test status: Passed

1.29.1 Description Verifies the rotation about Z-axis, the vertical displacement and the horizontal displacement on several points of a double hinged thin arc in planar bending.

1.29.2 Background


Double hinged thin arc in planar bending Scale = 1/8 01-0029SSLLB_FEM

Units

I. S.

Geometry


► de = 0.02 m, ► di = 0.016 m, ► A = 1.131 x 10-4 m2, ► Ix = 4.637 x 10-9 m4.


110


■ Longitudinal elastic modulus: E = 2 x 1011 Pa, ■ Poisson's ratio: ν = 0.3.

Boundary conditions

■ Outer: ► Hinge at A, ► At B: allowed rotation along z, vertical displacement restrained along y.

■ Inner: None.

Loading

■ External: Punctual load at C: Fy = F = - 100 N. ■ Internal: None.

1.29.2.2 Displacements at A, B and C

Reference solution

■ Rotation about z-axis

θA = - θB = ( π2 - 1)

FR22EI

■ Displacement;

Vertical at C: vC = π8

FREA + (

3π4 - 2)

FR3

2EI

Horizontal at B: uB = FR

2EA - FR3

2EI




111

Displacements shape

Fixed thin arc in planar bending Scale = 1/11 Deformed


Solver Result name Result description Reference value CM2 RY Rotation about Z-axis in point A [rad] 0.030774 CM2 RY Rotation about Z-axis in point B [rad] -0.030774 CM2 DZ Vertical displacement in point C [cm] -1.9206 CM2 DX Horizontal displacement in point B [cm] 5.3912


Result name Result description Value Error RY Rotation about Z-axis in point A [rad] 0.0307785 Rad 0.01% RY Rotation about Z-axis in point B [rad] -0.0307785 Rad -0.01% DZ Vertical displacement in point C [cm] -1.92019 cm 0.02% DX Horizontal displacement in point B [cm] 5.386 cm -0.10%


112

1.30 Portal frame with lateral connections (01-0030SSLLB_FEM)

Test ID: 2462

Test status: Passed

1.30.1 Description Verifies the rotation about z-axis and the bending moment on a portal frame with lateral connections.

1.30.2 Background


Portal frame with lateral connections Scale = 1/21 01-0030SSLLB_FEM

Units

I. S.

Geometry

Beam Length Moment of inertia AB lAB = 4 m IAB =

643 x 10-8 m4

AC lAC = 1 m IAC = 112 x 10-8 m4

AD lAD = 1 m IAD = 112 x 10-8 m4

AE lAE = 2 m IAE = 43 x 10-8 m4


113

■ G is in the middle of DA. ■ The beams have square sections:

► AAB = 16 x 10-4 m ► AAD = 1 x 10-4 m ► AAC = 1 x 10-4 m ► AAE = 4 x 10-4 m


Longitudinal elastic modulus: E = 2 x 1011 Pa,

Boundary conditions

■ Outer: ► Fixed at B, D and E, ► Hinge at C,

■ Inner: None.

Loading

■ External: ► Punctual force at G: Fy = F = - 105 N, ► Distributed load on beam AD: p = - 103 N/m.

■ Internal: None.

1.30.2.2 Displacements at A

Reference solution

Rotation at A about z-axis:

We say: kAn = EIAnlAn

where n = B, C, D or E

K = kAB + kAD + kAE + 34 kAC

rAn = kAnK

C1 = FlAD

8 - plAB

2

12

θ = C14K




114

Displacements shape

Portal frame with lateral connections Deformed

1.30.2.3 Moments in A

Reference solution

■ MAB = plAB

2

12 + rAB x C1

■ MAD = - FlAD

8 + rAD x C1

■ MAE = rAE x C1

■ MAC = rAC x C1




Solver Result name Result description Reference value CM2 RY Rotation θ about z-axis in point A [rad] -0.227118 CM2 My Bending moment in point A (MAB) [Nm] 11023.72 CM2 My Bending moment in point A (MAC) [Nm] 113.559 CM2 My Bending moment in point A (MAD) [Nm] 12348.588 CM2 My Bending moment in point A (MAE) [Nm] 1211.2994


Result name Result description Value Error RY Rotation Theta about z-axis in point A [rad] -0.227401 Rad -0.12% My Bending moment in point A (Moment AB) [Nm] 11021 N*m -0.02% My Bending moment in point A (Moment AC) [Nm] 113.704 N*m 0.13% My Bending moment in point A (Moment AD) [Nm] 12347.5 N*m -0.01% My Bending moment in point A (Moment AE) [Nm] 1212.77 N*m 0.12%


115

1.31 Truss with hinged bars under a punctual load (01-0031SSLLB_FEM)

Test ID: 2463

Test status: Passed

1.31.1 Description Verifies the horizontal and the vertical displacement in several points of a truss with hinged bars, subjected to a punctual load.

1.31.2 Background ■ Reference: Structure Calculation Software Validation Guide, test SSLL 11/89; ■ Analysis type: static linear (plane problem); ■ Element type: linear.

1.31.2.1 Model description

Truss with hinged bars under a punctual load Scale = 1/10 01-0031SSLLB_FEM

Units

I. S.

Geometry

Elements Length (m) Area (m2) AC 0.5 2 2 x 10-4 CB 0.5 2 2 x 10-4 CD 2.5 1 x 10-4 BD 2 1 x 10-4


116



Boundary conditions

■ Outer: Hinge at A and B, ■ Inner: None.

Loading

■ External: Punctual force at D: Fy = F = - 9.81 x 103 N. ■ Internal: None.

1.31.2.2 Displacements at C and D

Reference solution

Displacement method.



Displacements shape

Truss with hinged bars under a punctual load Scale = 1/9 Deformed


117


Solver Result name Result description Reference value CM2 DX Horizontal displacement in point C [mm] 0.26517 CM2 DX Horizontal displacement in point D [mm] 3.47902 CM2 DZ Vertical displacement in point C [mm] 0.08839 CM2 DZ Vertical displacement in point D [mm] -5.60084


Result name Result description Value Error DX Horizontal displacement in point C [mm] 0.264693 mm -0.18% DX Horizontal displacement in point D [mm] 3.47531 mm -0.11% DZ Vertical displacement in point C [mm] 0.0881705 mm -0.25% DZ Vertical displacement in point D [mm] -5.595 mm 0.10%


118

1.32 Beam on elastic soil, free ends (01-0032SSLLB_FEM)

Test ID: 2464

Test status: Passed

1.32.1 Description A beam under 3 punctual loads lays on a soil of constant linear stiffness. The bending moment, vertical displacement and rotation about z-axis on several points of the beam are verified.

1.32.2 Background


Beam on elastic soil, free ends Scale = 1/21 01-0032SSLLB_FEM

Units

I. S.

Geometry

■ L = (π 10 )/2, ■ I = 10-4 m4.


119



Boundary conditions

■ Outer: ► Free A and B extremities, ► Constant linear stiffness of soil ky = K = 840000 N/m2.

■ Inner: None.

Loading

■ External: Punctual load at A, C and B: Fy = F = - 10000 N. ■ Internal: None.

1.32.2.2 Bending moment and displacement at C

Reference solution

β = 4

K/(4EI)

ϕ = βL/2

λ = sh (2ϕ) + sin (2ϕ)

■ Bending moment: MC = (F/(4β))(ch(2ϕ) - cos (2ϕ) – 8sh(ϕ)sin(ϕ))/λ

■ Vertical displacement: vC = - (Fβ/(2K))( ch(2ϕ) + cos (2ϕ) + 8ch(ϕ)cos(ϕ) + 2)/λ



Bending moment diagram

Beam on elastic soil, free ends Scale = 1/20 Bending moment


120

1.32.2.3 Displacements at A

Reference solution

■ Vertical displacement: vA = (2Fβ/K)( ch(ϕ)cos(ϕ) + ch(2ϕ) + cos(2ϕ))/λ

■ Rotation about z-axis θA = (-2Fβ2/K)( sh(ϕ)cos(ϕ) - sin(ϕ)ch(ϕ) + sh(2ϕ) - sin(2ϕ))/λ




Solver Result name Result description Reference value CM2 My Bending moment in point C [Nm] 5759 CM2 Dz Vertical displacement in point C [m] -0.006844 CM2 Dz Vertical displacement in point A [m] -0.007854 CM2 RY Rotation θ about z-axis in point A [rad] -0.000706


Result name Result description Value Error My Bending moment in point C [Nm] 5779.54 N*m 0.36% Dz Vertical displacement in point C [m] -0.00684369 m 0.00% Dz Vertical displacement in point A [m] -0.00786073 m -0.09% RY Rotation Theta about z-axis in point A [rad] -0.000707427 Rad -0.20%


121

1.33 EDF Pylon (01-0033SFLLA_FEM)

Test ID: 2465

Test status: Passed

1.33.1 Description Verifies the displacement at the top of an EDF Pylon and the dominating buckling results. Three punctual loads corresponding to wind loads are applied on the main arms, on the upper arm and on the lower horizontal frames of the pylon.

1.33.2 Background

1.33.2.1 Model description ■ Reference: Internal GRAITEC test; ■ Analysis type: static linear, Eulerian buckling; ■ Element type: linear

Units

I. S.

Geometry



Boundary conditions

■ Outer: ► Hinged support, ► For the modeling, a fixed restraint and 4 beams were added at the pylon supports level.

■ Inner: None.


122

Loading

■ External: Punctual loads corresponding to a wind load.

► FX = 165550 N, FY = - 1240 N, FZ = - 58720 N on the main arms, ► FX = 50250 N, FY = - 1080 N, FZ = - 12780 N on the upper arm, ► FX = 11760 N, FY = 0 N, FZ = 0 N on the lower horizontal frames

■ Internal: None.


Reference solution


123

Software ANSYS 5.3 NE/NASTRAN 7.0 Max deflection (m) 0.714 0.714 λ dominating mode 2.77 2.77



Deformed shape


124

Buckling modal deformation (dominating mode)


Solver Result name Result description Reference value CM2 D Displacement at the top of the pylon [m] 0.714 CM2 Dominating buckling - critical λ, mode 4 [Hz] 2.77


Result name Result description Value Error D Displacement at the top of the pylon [m] 0.71254 m -0.20% Dominating buckling - critical Lambda - mode 4 [Hz] 2.83 Hz 2.12%


125

1.34 Beam on elastic soil, hinged ends (01-0034SSLLB_FEM)

Test ID: 2466

Test status: Passed

1.34.1 Description A beam under a punctual load, a distributed load and two torques lays on a soil of constant linear stiffness. The rotation around z-axis, the vertical reaction, the vertical displacement and the bending moment are verified in several points.

1.34.2 Background


Beam on elastic soil, hinged ends Scale = 1/27 01-0034SSLLB_FEM

Units

I. S.

Geometry

■ L = (π 10 )/2, ■ I = 10-4 m4.


126



Boundary conditions

■ Outer: ► Free A and B ends, ► Soil with a constant linear stiffness ky = K = 840000 N/m2.

■ Inner: None.

Loading

■ External: ► Punctual force at D: Fy = F = - 10000 N, ► Uniformly distributed force from A to B: fy = p = - 5000 N/m, ► Torque at A: Cz = -C = -15000 Nm, ► Torque at B: Cz = C = 15000 Nm.

■ Internal: None.

1.34.2.2 Displacement and support reaction at A

Reference solution

β = 4

K/(4EI)

ϕ = βL/2

λ = ch(2ϕ) + cos(2ϕ)

■ Vertical support reaction:

VA = -p(sh(2ϕ) + sin(2ϕ)) - 2βFch(ϕ)cos(ϕ) + 2β2C(sh(2ϕ) - sin(2ϕ)) x 1

2βλ

■ Rotation about z-axis:

θA = p(sh(2ϕ) – sin(2ϕ)) + 2βFsh(ϕ)sin(ϕ) - 2β2C(sh(2ϕ) + sin(2ϕ)) x 1

(K/β)λ




127

Deformed shape

Beam on elastic soil, hinged ends Scale = 1/20 Deformed

1.34.2.3 Displacement and bending moment at D

Reference solution

■ Vertical displacement:

vD = 2p(λ - 2ch(ϕ)cos(ϕ)) + βF(sh(2ϕ) – sin(2ϕ)) - 8β2Csh(ϕ)sin(ϕ) x 1

2Kλ

■ Bending moment:

MD = 4psh(ϕ)sin(ϕ) + βF(sh(2ϕ) + sin(2ϕ)) - 8β2Cch(ϕ)cos(ϕ) x 1

4β2λ




128

Bending moment diagram

Beam on elastic soil, hinged ends Scale = 1/20 Bending moment


Solver Result name Result description Reference value CM2 RY Rotation around z-axis in point A [rad] 0.003045 CM2 Fz Vertical reaction in point A [N] -11674 CM2 Dz Vertical displacement in point D [cm] -0.423326 CM2 My Bending moment in point D [Nm] -33840


Result name Result description Value Error RY Rotation around z-axis in point A [rad] 0.00304333 Rad -0.05% Fz Vertical reaction in point A [N] -11709 N -0.30% Dz Vertical displacement in point D [cm] -0.423297 cm 0.01% My Bending moment in point D [Nm] -33835.9 N*m 0.01%


129

1.35 Simply supported square plate (01-0036SSLSB_FEM)

Test ID: 2467

Test status: Passed

1.35.1 Description Verifies the vertical displacement in the center of a simply supported square plate.

1.35.2 Background

1.35.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 02/89; ■ Analysis type: static linear; ■ Element type: planar.

Simply supported square plate Scale = 1/9 01-0036SSLSB_FEM

Units

I. S.

Geometry

■ Side = 1 m, ■ Thickness h = 0.01m.




130

Boundary conditions

■ Outer: ► Simple support on the plate perimeter, ► For the modeling, we add a fixed support at B.

■ Inner: None.

Loading

■ External: Self weight (gravity = 9.81 m/s2). ■ Internal: None.

1.35.2.2 Vertical displacement at O

Reference solution

According to Love- Kirchhoff hypothesis, the displacement w at a point (x,y):

w(x,y) = Σ wmnsinmπxsinnπy

where wmn = 192ρg(1 - ν2)

mn(m2 + n2)π6Eh2



Deformed shape

Simply supported square plate Scale = 1/6 Deformed


Solver Result name Result description Reference value CM2 Dz Vertical displacement in point O [μm] -0.158


Result name Result description Value Error Dz Vertical displacement in point O [µm] -0.164901 µm -4.18%


131

1.36 Caisson beam in torsion (01-0037SSLSB_FEM)

Test ID: 2468

Test status: Passed

1.36.1 Description A torsion moment is applied on the free end of a caisson beam fixed on one end. For both ends, the displacement, the rotation about Z-axis and the stress are verified.

1.36.2 Background


Caisson beam in torsion Scale = 1/4 01-0037SSLSB_FEM

Units

I. S.

Geometry

■ Length; L = 1m, ■ Square section of side: b = 0.1 m, ■ Thickness = 0.005 m.




132

Boundary conditions

■ Outer: Beam fixed at end x = 0; ■ Inner: None.

Loading

■ External: Torsion moment M = 10N.m applied to the free end (for modeling, 4 forces of 50 N). ■ Internal: None.

1.36.2.2 Displacement and stress at two points

Reference solution

The reference solution is determined by averaging the results of several calculation software with implemented finite elements method.

Points coordinates:

■ A (0,0.05,0.5) ■ B (-0.05,0,0.8) Note: point O is the origin of the coordinate system (x,y,z).



Deformed shape

Caisson beam in torsion Scale = 1/4 Deformed


133


Solver Result name Result description Reference value CM2 D Displacement in point A [m] -0.617 x 10-6 CM2 D Displacement in point B [m] -0.987 x 10-6 CM2 RY Rotation about Z-axis in point A [rad] 0.123 x 10-4 CM2 RY Rotation about Z-axis in point B [rad] 0.197 x 10-4 CM2 sxy_mid σxy stress in point A [MPa] -0.11 CM2 sxy_mid σxy stress in point B [MPa] -0.11


Result name Result description Value Error D Displacement in point A [µm] 0.615909 µm -0.18% D Displacement in point B [µm] 0.986806 µm -0.02% RY Rotation about Z-axis in point A [rad] -1.23211e-005 Rad -0.17% RY Rotation about Z-axis in point B [rad] -1.97172e-005 Rad -0.09% sxy_mid Sigma xy stress in point A [MPa] -0.100037 MPa -0.04% sxy_mid Sigma xy stress in point B [MPa] -0.100212 MPa -0.21%


134

1.37 Thin cylinder under a uniform radial pressure (01-0038SSLSB_FEM)

Test ID: 2469

Test status: Passed

1.37.1 Description Verifies the stress, the radial deformation and the longitudinal deformation of a cylinder loaded with a uniform internal pressure.

1.37.2 Background

1.37.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 06/89; ■ Analysis type: static elastic; ■ Element type: planar.

Thin cylinder under a uniform radial pressure Scale = 1/18 01-0038SSLSB_FEM

Units

I. S.

Geometry

■ Length: L = 4 m, ■ Radius: R = 1 m, ■ Thickness: h = 0.02 m.




135

Boundary conditions

■ Outer: ► Free conditions ► For the modeling, only ¼ of the cylinder is considered and the symmetry conditions are applied. On the

other side, we restrained the displacements at a few nodes in order to make the model stable. ■ Inner: None.

Loading

■ External: Uniform internal pressure: p = 10000 Pa, ■ Internal: None.

1.37.2.2 Stresses in all points

Reference solution

Stresses in the planar elements coordinate system (x axis is parallel with the length of the cylinder):

■ σxx = 0

■ σyy = pRh



1.37.2.3 Cylinder deformation in all points ■ Radial deformation:

δR = pR2Eh

■ Longitudinal deformation:

δL = -pRνL

Eh


Solver Result name Result description Reference value CM2 syy_mid σyy stress in all points [Pa] 500000.000000 CM2 Dz δL radial deformation of the cylinder in all points [µm] 2.380000 CM2 DY δL longitudinal deformation of the cylinder in all points [µm] -2.860000


Result name Result description Value Error syy_mid Sigma yy stress in all points [Pa] 499521 Pa -0.10% Dz Delta R radial deformation of the cylinder in all points [µm] 2.39213 µm 0.51% DY Delta L longitudinal deformation of the cylinder in all points [µm] -2.85445 µm 0.19%


136

1.38 Square plate under planar stresses (01-0039SSLSB_FEM)

Test ID: 2470

Test status: Passed

1.38.1 Description Verifies the vertical displacement and the stresses on a square plate of 2 x 2 m, fixed on 3 sides with a uniform surface load on its surface.

1.38.2 Background

1.38.2.1 Model description ■ Reference: Internal GRAITEC test; ■ Analysis type: static linear; ■ Element type: planar (membrane).

Square plate under planar stresses Scale = 1/19 Modeling

[ ]1;1, −∈ηξ

Units

I. S.

Geometry

■ Thickness: e = 1 m, ■ 4 square elements of side h = 1 m.




137

Boundary conditions

■ Outer: Fixed on 3 sides, ■ Inner: None.

Loading

■ External: Uniform load p = -1. 108 N/ml on the upper surface, ■ Internal: None.


Reference solution

The reference displacements are calculated on nodes 7 and 9.

v9 = -6ph(3 + ν)(1 - ν2)

E(8(3 - ν)2 - (3 + ν)2) = -0.1809 x 10-3 m,

v7 = 4(3 - ν)3 + ν v9 = -0.592 x 10-3 m,

For element 1.4:

(For the stresses calculated above, the abscissa point (x = 0; y = 0) corresponds to node 8.)

σyy = E

1 - ν2 (v9 - v7)

2h (1 + ξ) for

σxx = νσyy for

σxy = E

1 + ν (v9 + v7) + η(v9 - v7)

4h (1 + ξ) for


■ Planar element: membrane, imposed mesh, ■ 9 nodes, ■ 4 surface quadrangles.

ξ = -1 ; σxx = 0 ξ = 0 ; σxx = -14.23 MPa ξ = 1 ; σxx = -28.46 MPa

η = -1 ; ξ = 0 ; σxy = -47.82 MPa η = 0 ; ξ = 0 ; σxy = -31.21 MPa η= 1 ; ξ = 0 ; σxy = -14.61 MPa

ξ = -1 ; σyy = 0 ξ = 0 ; σyy = -47.44 MPa ξ = 1 ; σyy = -94.88 MPa


138

Deformed shape


Solver Result name Result description Reference value CM2 DZ Vertical displacement on node 7 [mm] -0.592 CM2 DZ Vertical displacement on node 5 [mm] -0.1809 CM2 sxx_mid σxx stresses on Element 1.4 in x = 0 m [MPa] 0 CM2 sxx_mid σxx stresses on Element 1.4 in x = 0.5 m [MPa] -14.23 CM2 sxx_mid σxx stresses on Element 1.4 in x = 1 m [MPa] -28.46 CM2 syy_mid σyy stresses on Element 1.4 in x = 0 m [MPa] 0 CM2 syy_mid σyy stresses on Element 1.4 in x = 0.5 m [MPa] -47.44 CM2 syy_mid σyy stresses on Element 1.4 in x = 1 m [MPa] -94.88 CM2 sxy_mid σxy stresses on Element 1.4 in y = 0 m [MPa] -14.66 CM2 sxy_mid σxy stresses on Element 1.4 in y = 1 m [MPa] -47.82


Result name Result description Value Error DZ Vertical displacement on node 7 [mm] -0.59203 mm -0.01% DZ Vertical displacement on node 5 [mm] -0.180898 mm 0.00% sxx_mid Sigma xx stresses on Element 1.4 in x = 0 m [MPa] 7.45058e-015 MPa 0.00% sxx_mid Sigma xx stresses on Element 1.4 in x = 0.5 m [MPa] -14.2315 MPa -0.01% sxx_mid Sigma xx stresses on Element 1.4 in x = 1 m [MPa] -28.463 MPa -0.01% syy_mid Sigma yy stresses on Element 1.4 in x = 0 m [MPa] 1.49012e-014 MPa 0.00% syy_mid Sigma yy stresses on Element 1.4 in x = 0.5 m [MPa] -47.4383 MPa 0.00% syy_mid Sigma yy stresses on Element 1.4 in x = 1 m [MPa] -94.8767 MPa 0.00%

sxy_mid Sigma xy stresses on Element 1.4 in y = 0 m [MPa] -14.611 MPa 0.34% sxy_mid Sigma xy stresses on Element 1.4 in y = 1 m [MPa] -47.8178 MPa 0.00%


139

1.39 Stiffen membrane (01-0040SSLSB_FEM)

Test ID: 2471

Test status: Passed

1.39.1 Description Verifies the horizontal displacement and the stress on a plate (8 x 12 cm) fixed in the middle on 3 supports with a punctual load at its free node.

1.39.2 Background

1.39.2.1 Model description ■ Reference: Klaus-Jürgen Bathe - Finite Element Procedures in Engineering Analysis, Example 5.13; ■ Analysis type: static linear; ■ Element type: planar (membrane).

[ ]1;1, −∈ηξ

Units

I. S.

Geometry

■ Thickness: e = 0.1 cm, ■ Length: l = 8 cm, ■ Width: B = 12 cm.


■ Longitudinal elastic modulus: E = 30 x 106 N/cm2, ■ Poisson's ratio: ν = 0.3.

Boundary conditions

■ Outer: Fixed on 3 sides, ■ Inner: None.

Loading

■ External: Uniform load Fx = F = 6000 N at A, ■ Internal: None.


140

1.39.2.2 Results of the model in the linear elastic range

Reference solution

Point B is the origin of the coordinate system used for the results positions.

( ) ( )

( )

( )⎪⎩

⎪⎨

⎧

−=−==−=−==

=−=+

+−=

⎪⎩

⎪⎨

⎧

==−====

===

⎪⎩

⎪⎨

⎧

==−====

==−

−=

=+

=+⎟⎟

⎠

⎞⎜⎜⎝

⎛+

+−

== −

MPa 96.17N/cm 1796 ;1MPa 98.8N/cm 898 ;0

0 ;1for 1

81

MPa 55.11N/cm 1155 ;1MPa 77.5N/cm 577 ;0

0 ;1for

MPa 49.38N/cm 3849 ;1MPa 24.19N/cm 1924 ;0

0 ;1for 1

21

3410.97510.367410.2

6000

211

12

3

2xy1

2xy1

xy1

1

2yy1

2yy1

yy1

11

2xx1

2xx1

xx1

21

466

222

σξσξ

σξξ

νσ

σηση

σηνσσ

σηση

σηη

νσ

νν

buE

auE

cm

aES

baeabE

FKFu

Axy

xxyy

Axx

A


■ Planar element: membrane, imposed mesh, ■ 6 nodes, ■ 2 quadrangle planar elements and 1 bar.

Deformed shape


141


Solver Result name Result description Reference value CM2 DX Horizontal displacement Element 1 in A [cm] 9.340000 CM2 sxx_mid σxx stress Element 1 in y = 0 cm [MPa] 38.490000 CM2 sxx_mid σxx stress Element 1 in y = 6 cm [MPa] 0 CM2 syy_mid σyy stress Element 1 in y = 0 cm [MPa] 11.550000 CM2 syy_mid σyy stress Element 1 in y = 6 cm [MPa] 0 CM2 sxy_mid σxy stress Element 1 in x = 0 cm [MPa] 0 CM2 sxy_mid σxy stress Element 1 in x = 4 cm [MPa] -8.980000 CM2 sxy_mid σxy stress Element 1 in x = 8 cm [MPa] -17.960000


Result name Result description Value Error DX Horizontal displacement Element 1 in A [µm] 9.33999 µm 0.00% sxx_mid Sigma xx stress Element 1 in y = 0 cm [MPa] 38.489 MPa 0.00% sxx_mid Sigma xx stress Element 1 in y = 6 cm [MPa] 3.63798e-015 MPa 0.00% syy_mid Sigma yy stress Element 1 in y = 0 cm [MPa] 11.5467 MPa -0.03% syy_mid Sigma yy stress Element 1 in y = 6 cm [MPa] -9.09495e-016 MPa 0.00% sxy_mid Sigma xy stress Element 1 in x = 0 cm [MPa] -2.96059e-015 MPa 0.00% sxy_mid Sigma xy stress Element 1 in x = 4 cm [MPa] -8.98076 MPa -0.01% sxy_mid Sigma xy stress Element 1 in x = 8 cm [MPa] -17.9615 MPa -0.01%


142

1.40 Beam on two supports considering the shear force (01-0041SSLLB_FEM)

Test ID: 2472

Test status: Passed

1.40.1 Description Verifies the vertical displacement on a 300 cm long beam, consisting of an I shaped profile of a total height of 20.04 cm, a 0.96 cm thick web and 20.04 cm wide / 1.46 cm thick flanges.

1.40.2 Background

1.40.2.1 Model description ■ Reference: Internal GRAITEC test; ■ Analysis type: static linear (plane problem); ■ Element type: linear.

Units

I. S.

Geometry

l = 300 cm h = 20.04 cm b= 20.04 cm tw = 1.46 cm tf = 0.96 cm Sx= 74.95 cm2 Iz = 5462 cm4 Sy = 16.43 cm2


■ Longitudinal elastic modulus: E = 2285938 daN/cm2, ■ Transverse elastic modulus G = 879207 daN/cm2 ■ Poisson's ratio: ν = 0.3.


143

Boundary conditions

■ Outer: ► Simple support on node 11, ► For the modeling, put an hinge at node 1 (instead of a simple support).

■ Inner: None.

Loading

■ External: Vertical punctual load P = -20246 daN at node 6, ■ Internal: None.

1.40.2.2 Vertical displacement of the model in the linear elastic range

Reference solution

The reference displacement is calculated in the middle of the beam, at node 6.

( )cm 017.1105.0912.0

43.163.012

22859384

300202465462228593848

30020246448

33

6 −=−−=

+

−+

−=+=

xx

xxx

xGSPl

EIPlv

shear

y

flexion

z

876876


■ Planar element: S beam, imposed mesh, ■ 11 nodes, ■ 10 linear elements.

Deformed shape


Solver Result name Result description Reference value CM2 DZ Vertical displacement at node 6 [cm] -1.017


Result name Result description Value Error DZ Vertical displacement at node 6 [cm] -1.01722 cm -0.02%


144

1.41 Thin cylinder under a uniform axial load (01-0042SSLSB_FEM)

Test ID: 2473

Test status: Passed

1.41.1 Description Verifies the stress, the longitudinal deformation and the radial deformation of a cylinder under a uniform axial load.

1.41.2 Background

1.41.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 07/89; ■ Analysis type: static elastic; ■ Element type: planar.

Thin cylinder under a uniform axial load Scale = 1/19 01-0042SSLSB_FEM

Units

I. S.

Geometry

■ Thickness: h = 0.02 m, ■ Length: L = 4 m, ■ Radius: R = 1 m.




145

Boundary conditions

■ Outer: ► Null axial displacement at the left end: vz = 0, ► For the modeling, only a ¼ of the cylinder is considered.

■ Inner: None.

Loading

■ External: Uniform axial load q = 10000 N/m ■ Inner: None.

1.41.2.2 Stress in all points

Reference solution

x axis of the local coordinate system of planar elements is parallel to the cylinders axis.

σxx = qh

σyy = 0


■ Planar element: shell, imposed mesh, ■ 697 nodes, ■ 640 surface quadrangles.

1.41.2.3 Cylinder deformation at the free end

Reference solution

■ δL longitudinal deformation of the cylinder:

δL = qLEh

■ δR radial deformation of the cylinder:

δR = -qνREh




146

Deformation shape

Thin cylinder under a uniform axial load Scale = 1/22 Deformation shape


Solver Result name Result description Reference value CM2 sxx_mid σxx stress at all points [Pa] 5 x 105 CM2 syy_mid σyy stress at all points [Pa] 0 CM2 DY δL longitudinal deformation at the free end [m] 9.52 x 10-6 CM2 Dz δR radial deformation at the free end [m] -7.14 x 10-7


Result name Result description Value Error sxx_mid Sigma xx stress at all points [Pa] 500000 Pa 0.00% syy_mid Sigma yy stress at all points [Pa] 1.05305e-009 Pa 0.00% DY Delta L longitudinal deformation at the free end [mm] -0.00952381 mm -0.04% Dz Delta R radial deformation at the free end [mm] 0.000710887 mm -0.44%


147

1.42 Thin cylinder under a hydrostatic pressure (01-0043SSLSB_FEM)

Test ID: 2474

Test status: Passed

1.42.1 Description Verifies the stress, the longitudinal deformation and the radial deformation of a thin cylinder under a hydrostatic pressure.

1.42.2 Background

1.42.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 08/89; ■ Analysis type: static, linear elastic; ■ Element type: planar.

Thin cylinder under a hydrostatic pressure Scale = 1/25 01-0043SSLSB_FEM

Units

I. S.

Geometry





148

Boundary conditions

■ Outer: For the modeling, we consider only a quarter of the cylinder, so we impose the symmetry conditions on the nodes that are parallel with the cylinder’s axis.

■ Inner: None.

Loading

■ External: Radial internal pressure varies linearly with the "p" height, p = p0 zL ,

■ Internal: None.

1.42.2.2 Stresses

Reference solution


σxx = 0

σyy = p0RzLh



1.42.2.3 Cylinder deformation

Reference solution


δL = -p0Rνz2

2ELh

■ δL radial deformation of the cylinder:

δR = p0R2zELh




149

Deformation shape

Thin cylinder under a hydrostatic pressure Deformed


Solver Result name Result description Reference value CM2 syy_mid σyy stress in z = L/2 [Pa] 500000.000000 CM2 DY δL longitudinal deformation of the cylinder at the inferior

extremity [mm] -0.002860

CM2 Dz δL radial deformation of the cylinder in z = L/2 [mm] 0.002380


Result name Result description Value Error syy_mid Sigma yy stress in z = L/2 [Pa] 504489 Pa 0.89% DY Delta L longitudinal deformation of the cylinder at the inferior

extremity [mm] -0.00285442 mm 0.20%

Dz Delta L radial deformation of the cylinder in z = L/2 [mm] 0.00238372 mm 0.16%


150

1.43 Thin cylinder under its self weight (01-0044SSLSB_MEF)

Test ID: 2475

Test status: Passed

1.43.1 Description Verifies the stress, the longitudinal deformation and the radial deformation of a thin cylinder subjected to its self weight only.

1.43.2 Background

1.43.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 09/89; ■ Analysis type: static, linear elastic; ■ Element type: planar. A cylinder of R radius and L length subject of self weight only.

Thin cylinder under its self weight Scale = 1/24 01-0044SSLSB_FEM

Units

I. S.

Geometry



■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa, ■ Poisson's ratio: ν = 0.3, ■ Density: γ = 7.85 x 104 N/m3.


151

Boundary conditions

■ Outer: ► Null axial displacement at z = 0, ► For the modeling, we consider only a quarter of the cylinder, so we impose the symmetry conditions on

the nodes that are parallel with the cylinder’s axis. ■ Inner: None.

Loading

■ External: Cylinder self weight, ■ Internal: None.

1.43.2.2 Stresses

Reference solution


σxx = γz

σyy = 0




Reference solution


δL = γz2

2E

■ δR radial deformation of the cylinder:

δR = -γνRz

E


Solver Result name Result description Reference value CM2 sxx_mid σxx stress for z = L [Pa] -314000.000000 CM2 DY δL longitudinal deformation for z = L [mm] 0.002990 CM2 Dz δR radial deformation for z = L[mm] -0.000440

* To obtain this result, you must generate a calculation note “Planar elements stresses by load case in neutral fiber" with results on center.


Result name Result description Value Error sxx_mid Sigma xx stress for z = L [Pa] -309143 Pa 1.57% DY Delta L longitudinal deformation for z = L [mm] 0.00298922 mm -0.03% Dz Delta R radial deformation for z = L [mm] -0.000443587 mm -0.81%


152

1.44 Torus with uniform internal pressure (01-0045SSLSB_FEM)

Test ID: 2476

Test status: Passed

1.44.1 Description Verifies the stress and the radial deformation of a torus with uniform internal pressure.

1.44.2 Background


Torus with uniform internal pressure

01-0045SSLSB_FEM

Units

I. S.

Geometry

■ Thickness: h = 0.02 m, ■ Transverse section radius: b = 1 m, ■ Average radius of curvature: a = 2 m.




153

Boundary conditions

■ Outer: For the modeling, only 1/8 of the cylinder is considered, so the symmetry conditions are imposed to end nodes.

■ Inner: None.

Loading

■ External: Uniform internal pressure p = 10000 Pa ■ Internal: None.

1.44.2.2 Stresses

Reference solution

(See stresses description on the first scheme of the overview)

If a – b ≤ r ≤ a + b

σ11 = pb2h

r + ar

σ22 = pb2h




Reference solution

■ δR radial deformation of the torus:

δR = pb

2Eh (r - ν(r + a))




Solver Result name Result description Reference value CM2 syy_mid σ11 stresses for r = a - b [Pa] 7.5 x 105 CM2 syy_mid σ11 stresses for r = a + b [Pa] 4.17 x 105 CM2 sxx_mid σ22 stress for all r [Pa] 2.50 x 105 CM2 Dz δL radial deformations of the torus for r = a - b [m] 1.19 x 10-7 CM2 Dz δL radial deformations of the torus for r = a + b [m] 1.79 x 10-6


Result name Result description Value Error syy_mid Sigma 11 stresses for r = a - b [Pa] 742770 Pa -0.97% syy_mid Sigma 11 stresses for r = a + b [Pa] 415404 Pa -0.38% sxx_mid Sigma 22 stress for all r [Pa] 250331 Pa 0.13% Dz Delta L radial deformations of the torus for r = a - b [mm] -0.000117352 mm 1.40% Dz Delta L radial deformations of the torus for r = a + b [mm] 0.00180274 mm 0.71%


154

1.45 Spherical shell under internal pressure (01-0046SSLSB_FEM)

Test ID: 2477

Test status: Passed

1.45.1 Description A spherical shell is subjected to a uniform internal pressure. The stress and the radial deformation are verified.

1.45.2 Background


Spherical shell under internal pressure 01-0046SSLSB_FEM

Units

I. S.

Geometry

■ Thickness: h = 0.02 m, ■ Radius: R2 = 1 m, ■ θ = 90° (hemisphere).


155



Boundary conditions

■ Outer: Simple support (null displacement along vertical displacement) on the shell perimeter.

For modeling, we consider only half of the hemisphere, so we impose symmetry conditions (DOF restrains placed in the vertical plane xy in translation along z and in rotation along x and y). In addition, the node at the top of the shell is restrained in translation along x to assure the stability of the structure during calculation).

■ Inner: None.

Loading

■ External: Uniform internal pressure p = 10000 Pa ■ Internal: None.

1.45.2.2 Stresses

Reference solution

(See stresses description on the first scheme of the overview)

If 0° ≤ θ ≤ 90°

σ11 = σ22 = pR2

2

2h


■ Planar element: shell, imposed mesh, ■ 343 nodes, ■ 324 planar elements.


Reference solution

■ δR radial deformation of the calotte:

δR = pR22 (1 - ν) sin θ

2Eh




156

Deformed shape

Spherical shell under internal pressure Scale = 1/11 Deformed


Solver Result name Result description Reference value CM2 sxx_mid σ11 stress for all θ [Pa] 2.50 x 105 CM2 syy_mid σ22 stress for all θ [Pa] 2.50 x 105 CM2 Dz δR radial deformations for θ = 90° [m] 8.33 x 10-7


Result name Result description Value Error sxx_mid Sigma 11 stress for all Theta [Pa] 250202 Pa 0.08% syy_mid Sigma 22 stress for all Theta [Pa] 249907 Pa -0.04% Dz Delta R radial deformations for Theta = 90° [mm] 0.000832794 mm -0.02%


157

1.46 Pinch cylindrical shell (01-0048SSLSB_FEM)

Test ID: 2478

Test status: Passed

1.46.1 Description A cylinder of length L is pinched by 2 diametrically opposite forces (F). The vertical displacement is verified.

1.46.2 Background ■ Reference: Structure Calculation Software Validation Guide, test SSLS 20/89; ■ Analysis type: static, linear elastic; ■ Element type: planar.

1.46.2.1 Model description A cylinder of length L is pinched by 2 diametrically opposite forces (F).

Pinch cylindrical shell 01-0048SSLSB_FEM

Units

I. S.

Geometry

■ Length: L = 10.35 m (total length), ■ Radius: R = 4.953 m, ■ Thickness: h = 0.094 m.


158



Boundary conditions

■ Outer: For the modeling, we consider only half of the cylinder, so we impose symmetry conditions (nodes in the horizontal xz plane are restrained in translation along y and in rotation along x and z),

■ Inner: None.

Loading

■ External: 2 punctual loads F = 100 N, ■ Internal: None.

1.46.2.2 Vertical displacement at point A

Reference solution

The reference solution is determined by averaging the results of several calculation software with implemented finite elements method. 2% uncertainty about the reference solution.



1.46.2.3 Theoretical result

Solver Result name Result description Reference value CM2 DZ Vertical displacement in point A [m] -113.9 x 10-3


Result name Result description Value Error DZ Vertical displacement in point A [mm] -113.3 mm 0.53%


159

1.47 Spherical shell with holes (01-0049SSLSB_FEM)

Test ID: 2479

Test status: Passed

1.47.1 Description A spherical shell with holes is subjected to 4 forces, opposite 2 by 2. The horizontal displacement is verified.

1.47.2 Background ■ Reference: Structure Calculation Software Validation Guide, test SSLS 21/89; ■ Analysis type: static, linear elastic; ■ Element type: planar.

1.47.2.1 Model description

Spherical shell with holes 01-0049SSLSB_FEM

Units

I. S.

Geometry

■ Radius: R = 10 m ■ Thickness: h = 0.04 m, ■ Opening angle of the hole: ϕ0 = 18°.


160



Boundary conditions

■ Outer: For modeling, we consider only a quarter of the shell, so we impose symmetry conditions (nodes in the vertical yz plane are restrained in translation along x and in rotation along y and z. Nodes on the vertical xy plane are restrained in translation along z and in rotation along x and y),

■ Inner: None.

Loading

■ External: Punctual loads F = 1 N, according to the diagram, ■ Internal: None.

1.47.2.2 Horizontal displacement at point A

Reference solution




Deformed shape

Spherical shell with holes Scale = 1/79 Deformed


161

1.47.2.3 Theoretical background

Solver Result name Result description Reference value CM2 DX Horizontal displacement at point A(R,0,0) [mm] 94.0


Result name Result description Value Error DX Horizontal displacement at point A(R,0,0) [mm] 92.6205 mm -1.49%


162

1.48 Spherical dome under a uniform external pressure (01-0050SSLSB_FEM)

Test ID: 2480

Test status: Passed

1.48.1 Description A spherical dome of radius (a) is subjected to a uniform external pressure. The horizontal displacement and the external meridian stresses are verified.

1.48.2 Background


Spherical dome under a uniform external pressure

01-0050SSLSB_FEM

Units

I. S.

Geometry

■ Radius: a = 2.54 m, ■ Thickness: h = 0.0127 m, ■ Angle: θ = 75°.


163



Boundary conditions

■ Outer: Fixed on the dome perimeter, ■ Inner: None.

Loading

■ External: Uniform pressure p = 0.6897 x 106 Pa, ■ Internal: None.

1.48.2.2 Horizontal displacement and exterior meridian stress

Reference solution




Deformed shape


164


Solver Result name Result description Reference value CM2 DX Horizontal displacements in ψ = 15° 1.73 x 10-3 CM2 DX Horizontal displacements in ψ = 45° -1.02 x 10-3 CM2 syy_mid σyy external meridian stresses in ψ = 15° -74 CM2 sxx_mid σXX external meridian stresses in ψ = 45° -68


Result name Result description Value Error DX Horizontal displacements in Psi = 15° [mm] 1.73064 mm 0.04% DX Horizontal displacements in Psi = 45° [mm] -1.01367 mm 0.62% syy_mid Sigma yy external meridian stresses in Psi = 15° [MPa] -72.2609 MPa 2.41% sxx_mid Sigma XX external meridian stresses in Psi = 45° [MPa] -68.9909 MPa -1.44%


165

1.49 Simply supported square plate under a uniform load (01-0051SSLSB_FEM)

Test ID: 2481

Test status: Passed

1.49.1 Description A square plate simply supported is subjected to a uniform load. The vertical displacement and the bending moments at the plate center are verified.

1.49.2 Background


Simply supported square plate under a uniform load Scale = 1/9 01-0051SSLSB_FEM

Units

I. S.

Geometry

■ Side: a =b = 1 m, ■ Thickness: h = 0.01 m,



Boundary conditions

■ Outer: Simple support on the plate perimeter (null displacement along z-axis), ■ Inner: None


166

Loading

■ External: Normal pressure of plate p pZ = -1.0 Pa, ■ Internal: None.

1.49.2.2 Vertical displacement and bending moment at the center of the plate

Reference solution

Love-Kirchhoff thin plates theory.


■ Planar element: plate, imposed mesh, ■ 361 nodes, ■ 324 planar elements.

1.49.2.3 Theoretical result

Solver Result name Result description Reference value CM2 DZ Vertical displacement at plate center [m] -4.43 x 10-3 CM2 Mxx MX bending moment at plate center [Nm] 0.0479 CM2 Myy MY bending moment at plate center [Nm] 0.0479


Result name Result description Value Error DZ Vertical displacement at plate center [m] -0.00435847 m 1.64% Mxx Mx bending moment at plate center [Nm] 0.0471381 N*m -1.62% Myy My bending moment at plate center [Nm] 0.0471381 N*m -1.62%


167

1.50 Simply supported rectangular plate under a uniform load (01-0052SSLSB_FEM)

Test ID: 2482

Test status: Passed

1.50.1 Description A rectangular plate simply supported is subjected to a uniform load. The vertical displacement and the bending moments at the plate center are verified.

1.50.2 Background


Simply supported rectangular plate under a uniform load Scale = 1/11 01-0052SSLSB_FEM

Units

I. S.

Geometry

■ Width: a = 1 m, ■ Length: b = 2 m, ■ Thickness: h = 0.01 m,




168

Boundary conditions

■ Outer: Simple support on the plate perimeter (null displacement along z-axis), ■ Inner: None.

Loading

■ External: Normal pressure of plate p = pZ = -1.0 Pa, ■ Internal: None.


Reference solution




1.50.2.3 Theoretical background

Solver Result name Result description Reference value CM2 DZ Vertical displacement at plate center [m] -1.1060 x 10-2 CM2 Mxx MX bending moment at plate center [Nm] -0.1017 CM2 Myy MY bending moment at plate center [Nm] -0.0464


Result name Result description Value Error DZ Vertical displacement at plate center [cm] -1.10238 cm 0.33% Mxx Mx bending moment at plate center [Nm] -0.101737 N*m -0.04% Myy My bending moment at plate center [Nm] -0.0462457 N*m 0.33%


169

1.51 Simply supported rectangular plate under a uniform load (01-0053SSLSB_FEM)

Test ID: 2483

Test status: Passed

1.51.1 Description A rectangular plate simply supported is subjected to a uniform load. The vertical displacement and the bending moments at the plate center are verified.

1.51.2 Background


Simply supported rectangular plate under a uniform load Scale = 1/25 01-0053SSLSB_FEM

Units

I. S.

Geometry

■ Width: a = 1 m, ■ Length: b = 5 m, ■ Thickness: h = 0.01 m,



Boundary conditions

■ Outer: Simple support on the plate perimeter (null displacement along z-axis), ■ Inner: None.


170

Loading

■ External: Normal pressure of plate p = pZ = -1.0 Pa, ■ Internal: None.


Reference solution





Solver Result name Result description Reference value CM2 DZ Vertical displacement at plate center [m] 1.416 x 10-2 CM2 Mxx MX bending moment at plate center [Nm] 0.1246 CM2 Myy MY bending moment at plate center [Nm] 0.0375


Result name Result description Value Error DZ Vertical displacement at plate center [cm] -1.40141 cm 1.04% Mxx Mx bending moment at plate center [Nm] -0.124082 N*m 0.42% Myy My bending moment at plate center [Nm] -0.0375624 N*m -0.17%


171

1.52 Simply supported rectangular plate loaded with punctual force and moments (01-0054SSLSB_FEM)

Test ID: 2484

Test status: Passed

1.52.1 Description A rectangular plate simply supported is subjected to a punctual force and moments. The vertical displacement is verified.

1.52.2 Background


Simply supported rectangular plate loaded with punctual force and moments 01-0054SSLSB_FEM

Units

I. S.

Geometry

■ Width: DA = CB = 20 m, ■ Length: AB = DC = 5 m, ■ Thickness: h = 1 m,


■ Longitudinal elastic modulus: E =1000 Pa, ■ Poisson's ratio: ν = 0.3.

Boundary conditions

■ Outer: Punctual support at A, B and D (null displacement along z-axis), ■ Inner: None.


172

Loading

■ External: ► In A: MX = 20 Nm, MY = -10 Nm, ► In B: MX = 20 Nm, MY = 10 Nm, ► In C: FZ = -2 N, MX = -20 Nm, MY = 10 Nm, ► In D: MX = -20 Nm, MY = -10 Nm,

■ Internal: None.

1.52.2.2 Vertical displacement at C

Reference solution




Deformed shape

Simply supported rectangular plate loaded with punctual force and moments Deformed


Solver Result name Result description Reference value CM2 Dz Vertical displacement in point C [m] -12.480


Result name Result description Value Error Dz Vertical displacement in point C [m] -12.6677 m -1.48%


173

1.53 Shear plate perpendicular to the medium surface (01-0055SSLSB_FEM)

Test ID: 2485

Test status: Passed

1.53.1 Description Verifies the vertical displacement of a rectangular shear plate fixed at one end, loaded with two forces.

1.53.2 Background

1.53.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLS 27/89; ■ Analysis type: static; ■ Element type: planar.

Shear plate Scale = 1/50 01-0055SSLSB_FEM

Units

I. S.

Geometry

■ Length: L = 12 m, ■ Width: l = 1 m, ■ Thickness: h = 0.05 m,



Boundary conditions

■ Outer: Fixed AD edge, ■ Inner: None.


174

Loading

■ External: ► At B: Fz = -1.0 N, ► At C: FZ = 1.0 N,

■ Internal: None.


Reference solution




Deformed shape

Shear plate Scale = 1/35 Deformed


Solver Result name Result description Reference value CM2 Dz Vertical displacement in point C [m] 35.37 x 10-3


Result name Result description Value Error Dz Vertical displacement in point C [m] 35.6655 mm 0.83%


175

1.54 Triangulated system with hinged bars (01-0056SSLLB_FEM)

Test ID: 2486

Test status: Passed

1.54.1 Description A truss with hinged bars is placed on three punctual supports (subjected to imposed displacements) and is loaded with two punctual forces. A thermal load is applied to all the bars. The traction force and the vertical displacement are verified.

1.54.2 Background

1.54.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLL 12/89; ■ Analysis type: static (plane problem); ■ Element type: linear.

Units

I. S.

Geometry

■ θ = 30°, ■ Section A1 = 1.41 x 10-3 m2, ■ Section A2 = 2.82 x 10-3 m2.


■ Longitudinal elastic modulus: E =2.1 x 1011 Pa, ■ Coefficient of linear expansion: α = 10-5 °C-1.

Boundary conditions

■ Outer: ► Hinge at A (uA = vA = 0), ► Roller supports at B and C ( uB = v’C = 0),

■ Inner: None.


176

Loading

■ External: ► Support displacement: vA = -0.02 m ; vB = -0.03 m ; v’C = -0.015 m , ► Punctual loads: FE = -150 KN ; FF = -100 KN, ► Expansion effect on all bars for a temperature variation of 150° in relation with the assembly

temperature (specified geometry), ■ Internal: None.

1.54.2.2 Tension force in BD bar

Reference solution

Determining the hyperstatic unknown with the section cut method.


■ Linear element: S beam, automatic mesh, ■ 11 nodes, ■ 17 S beams + 1 rigid S beam for the modeling of the simple support at C.

1.54.2.3 Vertical displacement at D

Reference solution

vD displacement was determined by several software with implemented finite elements method.


■ Linear element: S beam, automatic mesh, ■ 11 nodes, ■ 17 S beams + 1 rigid S beam for the modeling of simple support at C.

Deformed shape

Triangulated system with hinged bars 01-0056SSLLB_FEM


Solver Result name Result description Reference value CM2 Fx FX traction force on BD bar [N] 43633 CM2 DZ Vertical displacement on point D [m] -0.01618


Result name Result description Value Error Fx Fx traction force on BD bar [N] 42870.9 N -1.78% DZ Vertical displacement on point D [m] -0.0162358 m -0.34%


177

1.55 A plate (0.01 m thick), fixed on its perimeter, loaded with a uniform pressure (01-0057SSLSB_FEM)

Test ID: 2487

Test status: Passed

1.55.1 Description Verifies the vertical displacement for a square plate (0.01 m thick), of side "a", fixed on its perimeter, loaded with a uniform pressure.

1.55.2 Background

1.55.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLV 09/89; ■ Analysis type: static; ■ Element type: planar.

Units

I. S.

Geometry

■ Side: a = 1 m, ■ Thickness: h = 0.01 m,

■ Slenderness: λ = ah = 100.


■ Reinforcement, ■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa, ■ Poisson's ratio: ν = 0.3.

Boundary conditions

■ Outer: Fixed sides: AB and BD,

For the modeling, we impose symmetry conditions at the CB side (restrained displacement along x and restrained rotation around y and z) and CD side (restrained displacement along y and restrained rotation around x and z),

■ Inner: None.


178

Loading

■ External: 1 MPa uniform pressure, ■ Internal: None.


Reference solution

This problem has a precise analytical solution only for thin plates. Therefore we propose the solutions obtained with Serendip elements with 20 nodes or thick plate elements of 4 nodes. The expected result should be between these values at ± 5%.




Solver Result name Result description Reference value CM2 Dz Vertical displacement in point C [m] -6.639 x 10-2


Result name Result description Value Error Dz Vertical displacement in point C [cm] -6.56563 cm 1.12%


179


Test ID: 2488

Test status: Passed


1.56.2 Background

1.56.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLV 09/89; ■ Analysis type: static; ■ Element type: planar. Square plate of side "a", for the modeling, only a quarter of the plate is considered.

Units

I. S.

Geometry





Boundary conditions

■ Outer: Fixed sides: AB and BD,


■ Inner: None.


180

Loading



Reference solution









181


Test ID: 2489

Test status: Passed


1.57.2 Background


Units

I. S.

Geometry





Boundary conditions

■ Outer: Fixed edges: AB and BD,


■ Inner: None.


182

Loading



Reference solution









183


Test ID: 2490

Test status: Passed


1.58.2 Background


Units

I. S.

Geometry





Boundary conditions



■ Inner: None.


184

Loading



Reference solution









185


Test ID: 2491

Test status: Passed


1.59.2 Background


Units

I. S.

Geometry





Boundary conditions



■ Inner: None.


186

Loading



Reference solution







Result name Result description Value Error Dz Vertical displacement in point C [mm] -0.0781846 mm 0.61%


187

1.60 A plate (0.01 m thick), fixed on its perimeter, loaded with a punctual force (01-0062SSLSB_FEM)

Test ID: 2492

Test status: Passed

1.60.1 Description Verifies the vertical displacement for a square plate (0.01 m thick), of side "a", fixed on its perimeter, loaded with a punctual force in the center.

1.60.2 Background ■ Reference: Structure Calculation Software Validation Guide, test SSLV 09/89; ■ Analysis type: static; ■ Element type: planar.

1.60.2.1 Model description Square plate of side "a".

0.01 m thick plate fixed on its perimeter Scale = 1/5 01-0062SSLSB_FEM

Units

I. S.

Geometry




188



Boundary conditions

■ Outer: Fixed edges, ■ Inner: None.

Loading

■ External: Punctual force applied on the center of the plate: FZ = -106 N, ■ Internal: None.

1.60.2.2 Vertical displacement at point C (center of the plate)

Reference solution





189


Solver Result name Result description Reference value CM2 DZ Vertical displacement in point C [m] -0.29579


Result name Result description Value Error DZ Vertical displacement in point C [m] -0.292146 m 1.25%


190


Test ID: 2493

Test status: Passed


1.61.2 Background



Units

I. S.

Geometry




191



Boundary conditions

■ Outer: Fixed sides, ■ Inner: None.

Loading

■ External: Punctual force applied on the center of the plate: FZ = -106 N, ■ Internal: None.

1.61.2.2 Vertical displacement at point C (the center of the plate)

Reference solution





192






193


Test ID: 2494

Test status: Passed


1.62.2 Background



Units

I. S.

Geometry

■ Side: a = 1 m, ■ Thickness: h = 0.02 m, ■ Slenderness: λ = 50.




194

Boundary conditions


Loading

■ External: punctual force applied in the center of the plate: FZ = -106 N, ■ Internal: None.

1.62.2.2 Vertical displacement at point C (the center of the plate)

Reference solution









195


Test ID: 2495

Test status: Passed


1.63.2 Background



Units

I. S.

Geometry





196

Boundary conditions

■ Outer: Fixed sides, ■ Inner: None.

Loading

■ External: Punctual force applied at the center of the plate: FZ = -106 N, ■ Internal: None.

1.63.2.2 Vertical displacement at point C center of the plate)

Reference solution





Solver Result name Result description Reference value CM2 DZ Vertical displacement in point C [m] -0.2595 x 10-2




197


Test ID: 2496

Test status: Passed


1.64.2 Background



Units

I. S.

Geometry





198

Boundary conditions


Loading

■ External: punctual force applied in the center of the plate: FZ = -106 N, ■ Internal: None.

1.64.2.2 Vertical displacement at point C (center of the plate)

Reference solution





Solver Result name Result description Reference value CM2 DZ Vertical displacement in point C [m] -0.42995 x 10-3


Result name Result description Value Error DZ Vertical displacement in point C [mm] -0.412094 mm 4.33%


199

1.65 Vibration mode of a thin piping elbow in space (case 1) (01-0067SDLLB_FEM)

Test ID: 2497

Test status: Passed

1.65.1 Description Verifies the eigen mode transverse frequencies for a thin piping elbow with a radius of 1 m, fixed on its ends and subjected to its self weight only.

1.65.2 Background

1.65.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 14/89; ■ Analysis type: modal analysis (space problem); ■ Element type: linear.

Vibration mode of a thin piping elbow Scale = 1/7 01-0067SDLLB_FEM

Units

I. S.

Geometry



200

■ Points coordinates (in m): ► O ( 0 ; 0 ; 0 ) ► A ( 0 ; R ; 0 ) ► B ( R ; 0 ; 0 )



Boundary conditions

■ Outer: Fixed at points A and B, ■ Inner: None.

Loading



Reference solution


■ transverse bending:

fj = μi

2

2π R2 GIpρA where i = 1,2.



Eigen mode shapes


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode Transverse 1 frequency [Hz] 44.23 CM2 Eigen mode Eigen mode Transverse 2 frequency [Hz] 125


Result name Result description Value Error Eigen mode Transverse 1 frequency [Hz] 44.12 Hz -0.25% Eigen mode Transverse 2 frequency [Hz] 120.09 Hz -4.09%


201


Test ID: 2498

Test status: Passed

1.66.1 Description Verifies the eigen mode transverse frequencies for a thin piping elbow with a radius of 1 m, extended with two straight elements (0.6 m long) and subjected to its self weight only.

1.66.2 Background

1.66.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 14/89; ■ Analysis type: modal analysis (in space); ■ Element type: linear.


Units

I. S.

Geometry

■ Average radius of curvature: OA = R = 1 m, ■ L = 0.6 m, ■ Straight circular hollow section: ■ Outer diameter: de = 0.020 m, ■ Inner diameter: di = 0.016 m, ■ Section: A = 1.131 x 10-4 m2, ■ Flexure moment of inertia relative to the y-axis: Iy = 4.637 x 10-9 m4, ■ Flexure moment of inertia relative to z-axis: Iz = 4.637 x 10-9 m4, ■ Polar inertia: Ip = 9.274 x 10-9 m4.


202




Boundary conditions

■ Outer: ► Fixed at points C and D ► In A: translation restraint along y and z, ► In B: translation restraint along x and z,

■ Inner: None.

Loading



Reference solution



fj = μi

2

2π R2 GIpρA where i = 1,2.



Eigen mode shapes


203


Solver Result name Result description Reference value CM2 Eigen mode Eigen mode Transverse 1 frequency [Hz] 33.4 CM2 Eigen mode Eigen mode Transverse 2 frequency [Hz] 100




204


Test ID: 2499

Test status: Passed

1.67.1 Description Verifies the eigen mode transverse frequencies for a thin piping elbow with a radius of 1 m, extended with two straight elements (2 m long) and subjected to its self weight only.

1.67.1.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 14/89; ■ Analysis type: modal analysis (space problem); ■ Element type: linear.


Units

I. S.

Geometry

■ Average radius of curvature: OA = R = 1 m, ■ L = 2 m, ■ Straight circular hollow section: ■ Outer diameter: de = 0.020 m, ■ Inner diameter: di = 0.016 m, ■ Section: A = 1.131 x 10-4 m2, ■ Flexure moment of inertia relative to the y-axis: Iy = 4.637 x 10-9 m4, ■ Flexure moment of inertia relative to z-axis: Iz = 4.637 x 10-9 m4, ■ Polar inertia: Ip = 9.274 x 10-9 m4.


205




Boundary conditions

■ Outer: ► Fixed at points C and D ► At A: translation restraint along y and z, ► At B: translation restraint along x and z,

■ Inner: None.

Loading



Reference solution



fj = μi

2

2π R2 GIpρA where i = 1,2 with i = 1,2:



Eigen mode shapes


206


Reference

Solver Result name Result description Reference value CM2 Eigen mode Eigen mode Transverse 1 frequency [Hz] 17.900 CM2 Eigen mode Eigen mode Transverse 2 frequency [Hz] 24.800




207

1.68 Reactions on supports and bending moments on a 2D portal frame (Rafters) (01-0077SSLPB_FEM)

Test ID: 2500

Test status: Passed

1.68.1 Description Moments and actions on supports calculation on a 2D portal frame. The purpose of this test is to verify the results of Advance Design for the M. R. study of a 2D portal frame.

1.68.2 Background

1.68.2.1 Model description ■ Reference: Design and calculation of metal structures. ■ Analysis type: static linear; ■ Element type: linear.


208

1.68.2.2 Moments and actions on supports M.R. calculation on a 2D portal frame. RDM results, for the linear load perpendicular on the rafters, are:

2qLVV EA == ( ) ( ) H

fh3f3k²hf5h8

32²qLHH EA =

++++

==

HhMM DB −== ( )fhH8

²qLMC +−=


Comparison between theoretical results and the results obtained by Advance Design for a linear load perpendicular on the chords

Solver Result name Result description Reference value CM2 Fz Vertical reaction V in A [DaN] -1000 CM2 Fz Vertical reaction V in E [DaN] -1000 CM2 Fx Horizontal reaction H in A [DaN] -332.9 CM2 Fx Horizontal reaction H in E [DaN] -332.9 CM2 My Moment in node B [DaNm] 2496.8 CM2 My Moment in node D [DaNm] -2496.8 CM2 My Moment in node C [DaNm] -1671


Result name Result description Value Error Fz Vertical reaction V on node A [daN] -1000 daN 0.00% Fz Vertical reaction V on node E [daN] -1000 daN 0.00% Fx Horizontal reaction H on node A [daN] -332.665 daN 0.07% Fx Horizontal reaction H on node E [daN] -332.665 daN 0.07% My Moment in node B [daNm] 2494.99 daN*m -0.07% My Moment in node D [daNm] -2494.99 daN*m 0.07% My Moment in node C [daNm] -1673.35 daN*m -0.14%


209

1.69 Reactions on supports and bending moments on a 2D portal frame (Columns) (01-0078SSLPB_FEM)

Test ID: 2501

Test status: Passed

1.69.1 Description Moments and actions on supports calculation on a 2D portal frame. The purpose of this test is to verify the results of Advance Design for the M. R. study of a 2D portal frame.

1.69.2 Background

1.69.2.1 Model description ■ Reference: Design and calculation of metal structures. ■ Analysis type: static linear; ■ Element type: linear.


210

1.69.2.2 Moments and reactions on supports M.R. calculation on a 2D portal frame. RDM results, for the linear load perpendicular on the column, are:

L2²qhVV EA −=−=

( )( ) ( )fh3f3k²h

fh26kh516

²qhHE +++++

= qhHH EA −=

hHqhM EB −=2

² ( )fhH

4²qhM EC +−= hHM ED −=


Solver Result name Result description Reference value CM2 Fz Vertical reaction V in A [DaN] 140.6 CM2 Fz Vertical reaction V in E [DaN] -140.6 CM2 Fx Horizontal reaction H in A [DaN] 579.1 CM2 Fx Horizontal reaction H in E [DaN] 170.9 CM2 My Moment in B [DaNm] -1530.8 CM2 My Moment in D [DaNm] -1281.7 CM2 My Moment in C [DaNm] 302.7


Result name Result description Value Error Fz Vertical reaction V on node A [daN] 140.625 daN 0.02% Fz Vertical reaction V on node E [daN] -140.625 daN -0.02% Fx Horizontal reaction H on node A [daN] 579.169 daN 0.01% Fx Horizontal reaction H on node E [daN] 170.831 daN -0.04% My Moment in node B [daNm] -1531.27 daN*m -0.03% My Moment in node D [daNm] -1281.23 daN*m 0.04% My Moment in node C [daNm] 302.063 daN*m -0.21%


211

1.70 Short beam on two hinged supports (01-0084SSLLB_FEM)

Test ID: 2502

Test status: Passed

1.70.1 Description Verifies the deflection magnitude on a non-slender beam with two hinged supports.

1.70.2 Background

1.70.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SSLL 02/89 ■ Analysis type: static linear (plane problem); ■ Element type: linear.

Units

I. S.

Geometry

■ Length: L = 1.44 m, ■ Area: A = 31 x 10-4 m² ■ Inertia: I = 2810 x 10-8 m4 ■ Shearing coefficient: az = 2.42 = A/Ar


■ E = 2 x 1011 Pa ■ ν = 0.3

Boundary conditions

■ Hinge at end x = 0, ■ Hinge at end x = 1.44 m.


212

Loading

Uniformly distributed force of p = -1. X 105 N/m on beam AB.

1.70.2.2 Reference results Calculation method used to obtain the reference solution

The deflection on the middle of a non-slender beam considering the shear force deformations given by the Timoshenko function:

GA8pl

EIpl

3845v

r

24

+=

where ( )υ+=

12EG and

zr a

AA =

where "Ar" is the reduced area and "az" the shear coefficient calculated on the transverse section.

Uncertainty about the reference: analytical solution:

Reference values

Point Magnitudes and units Value C V, deflection (m) -1.25926 x 10-3


Solver Result name Result description Reference value CM2 Dz Deflection magnitude in point C [m] -1.25926


Result name Result description Value Error Dz Deflection magnitude in node C [m] -0.00125926 m 0.00%


213

1.71 Slender beam of variable rectangular section with fixed-free ends (ß=5) (01-0085SDLLB_FEM)

Test ID: 2503

Test status: Passed

1.71.1 Description Verifies the eigen modes (bending) for a slender beam with variable rectangular section (fixed-free).

1.71.2 Background


Units

I. S.

Geometry

■ Length: L = 1 m, ■ Straight initial section:

► h0 = 0.04 m ► b0 = 0.05 m ► A0 = 2 x 10-3 m²

■ Straight final section ► h1 = 0.01 m ► b1 = 0.01 m ► A1 = 10-4 m²


■ E = 2 x 1011 Pa ■ ρ = 7800 kg/m3

Boundary conditions

■ Outer: ► Fixed at end x = 0, ► Free at end x = 1

■ Inner: None.

Loading



214

1.71.2.2 Reference results Calculation method used to obtain the reference solution

Precise calculation by numerical integration of the differential equation of beams bending (Euler-Bernoulli theories):

²t²A

²x²EIz

x2

2

δνδ

ρ−=⎟⎠

⎞⎜⎝

⎛δ

νδδδ

where Iz and A vary with the abscissa.

The result is:

( ) ρβαλπ

= 12E

²l1h,i

21fi with

⎪⎪⎩

⎪⎪⎨

⎧

=ο

=β

=ο

=α

51b

b

41h

h

λ1 λ2 λ3 λ4 λ5 β = 5 24.308 75.56 167.21 301.9 480.4


Reference values

Eigen mode type Frequency (Hz) 1 56.55 2 175.79 3 389.01 4 702.36

Flexion

5 1117.63

MODE 1 Scale = 1/4


215

MODE 2 Scale = 1/4

MODE 3 Scale = 1/4


216

MODE 4 Scale = 1/4

MODE 5 Scale = 1/4


Theoretical Frequency

Result name Result description Reference value

Eigen mode Frequency of eigen mode 1 [Hz] 56.55 Eigen mode Frequency of eigen mode 2 [Hz] 175.79 Eigen mode Frequency of eigen mode 3 [Hz] 389.01 Eigen mode Frequency of eigen mode 4 [Hz] 702.36 Eigen mode Frequency of eigen mode 5 [Hz] 1117.63


217


Result name Result description Value Error Frequency of eigen mode 1 [Hz] 58.49 Hz 3.32% Frequency of eigen mode 2 [Hz] 177.67 Hz 1.06% Frequency of eigen mode 3 [Hz] 388.85 Hz -0.04% Frequency of eigen mode 4 [Hz] 697.38 Hz -0.71% Frequency of eigen mode 5 [Hz] 1106.31 Hz -1.02%


218

1.72 Slender beam of variable rectangular section (fixed-fixed) (01-0086SDLLB_FEM)

Test ID: 2504

Test status: Passed

1.72.1 Description Verifies the eigen modes (flexion) for a slender beam with variable rectangular section (fixed-fixed).

1.72.2 BackgroundOverview


Units

I. S.

Geometry

■ Length: L = 0.6 m, ■ Constant thickness: h = 0.01 m ■ Initial section:

► b0 = 0.03 m ► A0 = 3 x 10-4 m²

■ Section variation: ► with (α = 1) ► b = b0e-2αx ► A = A0e-2αx


■ E = 2 x 1011 Pa ■ ν = 0.3 ■ ρ = 7800 kg/m3

Boundary conditions

■ Outer: ► Fixed at end x = 0, ► Fixed at end x = 0.6 m.

■ Inner: None.

Loading



219

1.72.2.2 Reference results

Calculation method used to obtain the reference solution

ωi pulsation is given by the roots of the equation:

( ) ( ) ( ) ( ) 0rlsinslshrs2

²r²sslchrlcos1 =−

+−

with

( ) 0²²s;²r;EIA 2

isi2

i2i

zo

2i04

i >α−λ⎯→⎯α−λ=λ+α=ωρ

=λ

Therefore, the ν translation components of φi(x) mode, are:

( ) ( ) ( ) ⎥⎦

⎤⎢⎣

⎡−

−−

+−=Φ α ))sx(rsh)rxsin(s()rlsin(s)sl(rsh

)sl(ch)rlcos(sxchrxcosex xi


Reference values

Eigen mode φi(x)* Eigen mode order

Frequency (Hz) x = 0 0.1 0.2 0.3 0.4 0.5 0.6

1 143.303 0 0.237 0.703 1 0.859 0.354 0 2 396.821 0 -0.504 -0.818 0 0.943 0.752 0 3 779.425 0 0.670 0.210 -0.831 0.257 1 0 4 1289.577 0 -0.670 0.486 0 -0.594 1 0

* φi(x) eigen modes* standardized to 1 at the point of maximum amplitude.

Eigen modes


220


Solver Result name Result description Reference value CM2 Eigen mode Frequency of eigen mode 1 [Hz] 143.303 CM2 Eigen mode Frequency of eigen mode 2 [Hz] 396.821 CM2 Eigen mode Frequency of eigen mode 3 [Hz] 779.425 CM2 Eigen mode Frequency of eigen mode 4 [Hz] 1289.577


Result name Result description Value Error Frequency of eigen mode 1 [Hz] 145.88 Hz 1.77% Frequency of eigen mode 2 [Hz] 400.26 Hz 0.86% Frequency of eigen mode 3 [Hz] 783.15 Hz 0.48% Frequency of eigen mode 4 [Hz] 1293.42 Hz 0.30%


221

1.73 Plane portal frame with hinged supports (01-0089SSLLB_FEM)

Test ID: 2505

Test status: Passed

1.73.1 Description Calculation of support reactions of a 2D portal frame with hinged supports.

1.73.2 Background


Units

I. S.

Geometry

■ Length: L = 20 m, ■ I1 = 5.0 x 10-4 m4 ■ a = 4 m ■ h = 8 m ■ b = 10.77 m ■ I2 = 2.5 x 10-4 m4


■ Isotropic linear elastic material. ■ E = 2.1 x 1011 Pa


222

Boundary conditions

Hinged base plates A and B (uA = vA = 0 ; uB = vB = 0).

Loading

■ p = -3 000 N/m ■ F1 = -20 000 N ■ F2 = -10 000 N ■ M = -100 000 Nm

1.73.2.2 Calculation method used to obtain the reference solution ■ K = (I2/b)(h/I1) ■ p = a/h ■ m = 1 + p ■ B = 2(K + 1) + m ■ C = 1 + 2m ■ N = B + mC ■ VA = 3pl/8 + F1/2 – M/l + F2h/l ■ HA = pl²(3 + 5m)/(32Nh) + (F1l/(4h))(C/N) + F2(1-(B + C)/(2N)) + (3M/h)((1 + m)/(2N))

1.73.2.3 Reference values Point Magnitudes and units Value

A V, vertical reaction (N) 31 500.0 A H, horizontal reaction (N) 20 239.4 C vc (m) -0.03072


Solver Result name Result description Reference value CM2 Fz Vertical reaction V in point A [N] -31500 CM2 Fx Horizontal reaction H in point A [N] -20239.4 CM2 DZ vc displacement in point C [m] -0.03072


Result name Result description Value Error Fz Vertical reaction V in point A [N] -31500 N 0.00% Fx Horizontal reaction H in point A [N] -20239.3 N 0.00% DZ Displacement in point C [m] -0.0307191 m 0.00%


223

1.74 Double fixed beam in Eulerian buckling with a thermal load (01-0091HFLLB_FEM)

Test ID: 2506

Test status: Passed

1.74.1 Description Verifies the normal force on the nodes of a double fixed beam in Eulerian buckling with a thermal load.

1.74.2 Background

1.74.2.1 Model description ■ Reference: Euler theory; ■ Analysis type: Eulerian buckling; ■ Element type: linear.

Units

I. S.

Geometry

L = 10 m

Cross Section Sx m² Sy m² Sz m² Ix m4 Iy m4 Iz m4 Vx m3 V1y m3 V1z m3 V2y m3 V2z m3

IPE200 0.002850 0.001400 0.001799 0.0000000646 0.0000014200 0.0000194300 0.00000000 0.00002850 0.00019400 0.00002850 0.00019400


■ Longitudinal elastic modulus: E = 2.1 x 1011 N/m2, ■ Poisson's ratio: ν = 0.3. ■ Coefficient of thermal expansion: α = 0.00001

Boundary conditions



224

Loading

■ External: Punctual load FZ = 1 N at = L/2 (load that initializes the deformed shape), ■ Internal: ΔT = 5°C corresponding to a compression force of:

kN 925.29500001.000285.011E1.2TESN =×××=Δα=


Reference solution


93.3724.117925.29k 724.117

2

P 2

2

critical ==⇒=

⎟⎠⎞

⎜⎝⎛

= λπ NLEI

Observation: in this case, the thermal load has no effect over the critical coefficient



Deformed shape of mode 1


Solver Result name Result description Reference value CM2 Fx Normal Force on Node 6 - Case 101 [kN] -29.925 CM2 Fx Normal Force on Node 6 - Case 102 [kN] -117.724


Result name Result description Value Error Fx Normal Force Fx on Node 6 - Case 101 [kN] -29.904 kN 0.07% Fx Normal Force Fx on Node 6 - Case 102 [kN] -118.081 kN -0.30%


225

1.75 Cantilever beam in Eulerian buckling with thermal load (01-0092HFLLB_FEM)

Test ID: 2507

Test status: Passed

1.75.1 Description Verifies the vertical displacement and the normal force on a cantilever beam in Eulerian buckling with thermal load.

1.75.2 Background

1.75.2.1 Model description ■ Reference: Euler theory; ■ Analysis type: Eulerian buckling; ■ Element type: linear.

Units

I. S.

Geometry

■ L = 10 m ■ S=0.01 m2 ■ I = 0.0002 m4


■ Longitudinal elastic modulus: E = 2.0 x 1010 N/m2, ■ Poisson's ratio: ν = 0.1. ■ Coefficient of thermal expansion: α = 0.00001

Boundary conditions


Loading

■ External: Punctual load P = -100000 N at x = L, ■ Internal: T = -50°C (Contraction equivalent to the compression force)

( 5000001.0T0005.001.010.2

100000ESN

100 −×=Δα==×

−==ε )


226


Reference solution


98696.010000098696 98696

4P 2

2

critical ==⇒== λπ NLEI

Observation: in this case, the thermal load has no effect over the critical coefficient



Deformed shape


Solver Result name Result description Reference value CM2 DZ Vertical displacement v5 on Node 5 - Case 101 [cm] -1.0 CM2 Fx Normal Force on Node A - Case 101 [N] -100000 CM2 Fx Normal Force on Node A - Case 102 [N] -98696


Result name Result description Value Error DZ Vertical displacement on Node 5 [cm] -1 cm 0.00% Fx Normal Force - Case 101 [N] -100000 N 0.00% Fx Normal Force - Case 102 [N] -98699.3 N 0.00%


227

1.76 A 3D bar structure with elastic support (01-0094SSLLB_FEM)

Test ID: 2508

Test status: Passed

1.76.1 Description A 3D bar structure with elastic support is subjected to a vertical load of -100 kN. The V2 magnitude on node 5, the normal force magnitude, the reaction magnitude on supports and the action magnitude are verified.

1.76.1.1 Model description ■ Reference: Internal GRAITEC; ■ Analysis type: static linear; ■ Element type: linear.

Units

I. S.

Geometry

For all bars:

■ H = 3 m ■ B = 3 m ■ S = 0.02 m2

Element Node i Node j 1 (bar) 1 5 2 (bar) 2 5 3 (bar) 3 5 4 (bar) 4 5

5 (spring) 5 6


■ Isotropic linear elastic materials ■ Longitudinal elastic modulus: E = 2.1 E8 N/m2,


228

Boundary conditions

■ Outer: At node 5: K = 50000 kN/m ; ■ Inner: None.

Loading

■ External: Vertical load at node: P = -100 kN, ■ Internal: None.


System solution

2

22 BHL += . Also, U1 = V1 = U5 = U6 = V6 = 0

■ Stiffness matrix of bar 1


229

( ) ( )

1L2x= where

.121.1

21)(.).1()(

−

++−=⇔+−=

ξ

ξξξ jiji uuuuLxu

Lxxu

in the local coordinate system:

[ ] [ ] [ ][ ] [ ] [ ]

)()()()(

0000010100000101

)()(

1111

41

41

41

41

2=

221

21

2121

1

1

1

101

j

j

i

i

j

i

L Te

T

v

vuvu

LES

uu

LESd

LES

dL

ESdxBBESdVBHBke

⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢

⎣

⎡

−

−

=⎥⎦

⎤⎢⎣

⎡−

−=

⎥⎥⎥

⎦

⎤

⎢⎢⎢

⎣

⎡

−

−

⎭⎬⎫

⎩⎨⎧−

⎪⎭

⎪⎬

⎫

⎪⎩

⎪⎨

⎧−===

∫

∫∫∫

−

−

ξ

ξ

where [ ]

)v()u()v()u(

0000010100000101

LESk

5

5

1

1

1

⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢

⎣

⎡

−

−

=

The elementary matrix [ ]ek expressed in the global coordinate system XY is the following: (θ angle allowing the transition from the global base to the local base):

[ ] [ ] [ ][ ] [ ]

[ ]

⎥⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢⎢

⎣

⎡

θθθθ−θθ−θθθθθ−θ−

θ−θθ−θθθθθ−θ−θθθ

=

⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢

⎣

⎡

θθ−θθ

θθ−θθ

==−

22

22

22

22

e

eeeT

ee

sinsincossinsincossincoscossincoscos

sinsincossinsincossincoscossincoscos

LESK

cossin00sincos00

00cossin00sincos

Ravec RkRK

Knowing that LHsin and

2cos == θθ

LB

, then:

⎪⎪⎪⎪

⎩

⎪⎪⎪⎪

⎨

⎧

=θθ

=θ

=θ

2

2

22

2

22

L2HBcossin

LHsin

L2Bcos

[ ]

)()()()(

22

2222

22

2222

:)DH(arctan =5,1 nodes 1element for

5

5

1

1

22

22

22

22

31

VUVU

HHBHHB

HBBHBB

HHBHHB

HBBHBB

LESK

⎥⎥⎥⎥⎥⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢⎢⎢⎢⎢⎢

⎣

⎡

−−

−−

−−

−−

=→ θ


230

■ Stiffness matrix of spring support 5

[ ]

)()()()(

0000010100000101

)()(

1111

:system coordinate local in the

4KKsay We

5

j

j

i

i

j

i

vuvu

Kuu

Kk

⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢

⎣

⎡

−

−

′=⎥⎦

⎤⎢⎣

⎡−

−′=

=′

[ ]

)()()()(

101000001010

0000

':90=6,5 nodes 5element for

6

6

5

5

5

VUVU

KK

⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢

⎣

⎡

−

−=°→ θ

■ System [ ]{ } { }FQK =

⎪⎪⎪⎪

⎭

⎪⎪⎪⎪

⎬

⎫

⎪⎪⎪⎪

⎩

⎪⎪⎪⎪

⎨

⎧

−=

⎪⎪⎪⎪

⎭

⎪⎪⎪⎪

⎬

⎫

⎪⎪⎪⎪

⎩

⎪⎪⎪⎪

⎨

⎧

⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢

⎣

⎡

′′−

′−′+−−

−−

−−

−−

6Y

6X

5X

1Y

1X

6

6

5

5

1

1

233

233

3

2

33

2

3

233

233

3

2

33

2

3

RR

PRRR

VUVUVU

K0K000000000

K0KHLES

2HB

LESH

LES

2HB

LES

002

HBLES

2B

LES

2HB

LES

2B

LES

00HLES

2HB

LESH

LES

2HB

LES

002

HBLES

2B

LES

2HB

LES

2B

LES

If U1 = V1 = U5 = U6 = V6 = 0, then:

m 001885.0

4KH

LES

4P

KHLES

4P

V2

32

3

5 −=+

−=

′+

−=

And N 23563V

4KRN 1436VH

LESR

0RN 1015V2

HBLESRN 1015V

2HB

LESR

56Y52

31Y

6X535X531X

=−==−=

=−===−=

Note:

■ The values on supports specified by Advance Design correspond to the actions, ■ RY6 calculated value must be multiplied by 4 in relation to the double symmetry,

■ x1 value is similar to the one found by Advance Design by dividing this by 2


231

Effort in bar 1:

⎭⎬⎫

⎩⎨⎧

−=

⎭⎬⎫

⎩⎨⎧

=⎭⎬⎫

⎩⎨⎧

⎥⎦

⎤⎢⎣

⎡−

−

⎪⎪⎭

⎪⎪⎬

⎫

⎪⎪⎩

⎪⎪⎨

⎧

⎥⎥⎥⎥⎥⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢⎢⎢⎢⎢⎢

⎣

⎡

−

−=

⎪⎪⎭

⎪⎪⎬

⎫

⎪⎪⎩

⎪⎪⎨

⎧

17591759

1111

and

200

200

002

002

5

1

5

1

5

5

1

1

5

5

1

1

NN

uu

LES

VUVU

LB

LH

LH

LB

LB

LH

LH

LB

vuvu

⎭⎬⎫

⎩⎨⎧

=⎭⎬⎫

⎩⎨⎧

⎥⎦

⎤⎢⎣

⎡−

−

⎪⎪⎭

⎪⎪⎬

⎫

⎪⎪⎩

⎪⎪⎨

⎧

⎥⎥⎥⎥

⎦

⎤

⎢⎢⎢⎢

⎣

⎡

−

−=

⎪⎪⎭

⎪⎪⎬

⎫

⎪⎪⎩

⎪⎪⎨

⎧

5

1

5

1

5

5

1

1

5

5

1

1

1111

and

cossin00sincos00

00cossin00sincos

NN

uu

LES

VUVU

vuvu

θθθθ

θθθθ

Reference values

Point Magnitude Units Value 5 V2 m -1.885 10-3

All bars Normal force N -1759 Supports 1, 3, 4 and 5 Fz action N -1436 Supports 1, 3, 4 and 5 Action Fx=Fy N 7182/1015 ±=

Support 6 Fz action N 23563 x 4=94253


■ Linear element: beam, automatic mesh, ■ 5 nodes, ■ 4 linear elements.


232

Deformed shape

Normal forces diagram


233

1.76.1.3 Reference values

Solver Result name Result description Reference value CM2 D V2 magnitude on node 5 [m] -1.885 10-3 CM2 Fx Normal force magnitude on bar 1 [N] -1759 CM2 Fx Normal force magnitude on bar 2 [N] -1759 CM2 Fx Normal force magnitude on bar 3 [N] -1759 CM2 Fx Normal force magnitude on bar 4 [N] -1759 CM2 Fz Fz reaction magnitude on support 1 [N] 1436 CM2 Fz Fz reaction magnitude on support 3 [N] 1436 CM2 Fz Fz reaction magnitude on support 4 [N] 1436 CM2 Fz Fz reaction magnitude on support 5 [N] 1436 CM2 Fx Action Fx magnitude on support 1 [N] -718 CM2 Fx Action Fx magnitude on support 3 [N] 718 CM2 Fx Action Fx magnitude on support 4 [N] 718 CM2 Fx Action Fx magnitude on support 5 [N] -718 CM2 Fy Action Fy magnitude on support 1 [N] -718 CM2 Fy Action Fy magnitude on support 3 [N] -718 CM2 Fy Action Fy magnitude on support 4 [N] 718 CM2 Fy Action Fy magnitude on support 5 [N] 718 CM2 Fz Fz reaction magnitude on support 6 [N] 23563 x 4=94253


Result name Result description Value Error D Displacement on node 5 [mm] 1.88508 mm 0.00% Fx Normal force magnitude on bar 1 [N] -1759.4 N -0.02% Fx Normal force magnitude on bar 2 [N] -1759.4 N -0.02% Fx Normal force magnitude on bar 3 [N] -1759.4 N -0.02% Fx Normal force magnitude on bar 4 [N] -1759.4 N -0.02% Fy Fz reaction magnitude on support 1 [N] 1436.55 N 0.04% Fy Fz reaction magnitude on support 2 [N] 1436.55 N 0.04% Fy Fz reaction magnitude on support 3 [N] 1436.55 N 0.04% Fy Fz reaction magnitude on support 4 [N] 1436.55 N 0.04% Fx Action Fx magnitude on support 1 [N] -718.274 N -0.04% Fx Action Fx magnitude on support 2 [N] 718.274 N 0.04% Fx Action Fx magnitude on support 3 [N] 718.274 N 0.04% Fx Action Fx magnitude on support 4 [N] -718.274 N -0.04% Fz Action Fy magnitude on support 1 [N] -718.274 N -0.04% Fz Action Fy magnitude on support 2 [N] -718.274 N -0.04% Fz Action Fy magnitude on support 3 [N] 718.274 N 0.04% Fz Action Fy magnitude on support 4 [N] 718.274 N 0.04% Fy Action Fy magnitude on support 6 [N] 94253.8 N 0.00%


234

1.77 Fixed/free slender beam with centered mass (01-0095SDLLB_FEM)

Test ID: 2509

Test status: Passed

1.77.1 Description Fixed/free slender beam with centered mass.

Tested functions: Eigen mode frequencies, straight slender beam, combined bending-torsion, plane bending, transverse bending, punctual mass.

1.77.2 Background ■ Reference: Structure Calculation Software Validation Guide, test SDLL 15/89; ■ Analysis type: modal analysis; ■ Element type: linear. ■ Tested functions: Eigen mode frequencies, straight slender beam, combined bending-torsion, plane bending,

transverse bending, punctual mass.

1.77.2.1 Test data

Units

I. S.

Geometry

■ Outer diameter de = 0.35 m, ■ Inner diameter: di = 0.32 m, ■ Beam length: l = 10 m, ■ Area: A = 1.57865 x 10-2 m2 ■ Polar inertia: IP = 4.43798 x 10-4m4 ■ Inertia: Iy = Iz = 2.21899 x 10-4m4 ■ Punctual mass: mc = 1000 kg ■ Beam self-weight: M


235


■ Longitudinal elastic modulus: E = 2.1 x 1011 Pa, ■ Density: ρ = 7800 kg/m3 ■ Poisson's ratio: ν=0.3 (this coefficient was not specified in the AFNOR test , the value 0.3 seems to be the

more appropriate to obtain the correct frequency value of mode No. 8 with NE/NASTRAN)

Boundary conditions

■ Outer: Fixed at point A, x = 0, ■ Inner: none

Loading

None for the modal analysis

1.77.2.2 Reference results

Reference frequency

For the first mode, the Rayleigh method gives the approximation formula

)M24.0m(IEI3

x2/1fc

3z

1 +Π=

Mode Shape Units Reference 1 Flexion Hz 1.65 2 Flexion Hz 1.65 3 Flexion Hz 16.07 4 Flexion Hz 16.07 5 Flexion Hz 50.02 6 Flexion Hz 50.02 7 Traction Hz 76.47 8 Torsion Hz 80.47 9 Flexion Hz 103.2 10 Flexion Hz 103.2

Comment: The mass matrix associated with the beam torsion on two nodes, is expressed as:

⎥⎦

⎤⎢⎣

⎡×

××ρ12/12/11

3Il P

And to the extent that Advance Design uses a condensed mass matrix, the value of the torsion mass inertia

introduced in the model is set to: 3

Il p××ρ

Uncertainty about the reference frequencies

■ Analytical solution mode 1 ■ Other modes: ± 1%


■ Linear element AB: Beam ■ Beam meshing: 20 elements.


236

Modal deformations


237

Observation: the deformed shape of mode No. 8 that does not really correspond to a torsion deformation, is actually the display result of the translations and not of the rotations. This is confirmed by the rotation values of the corresponding mode.

Eigen modes vector 8

Node DX DY DZ RX RY RZ 1 -3.336e-033 6.479e-031 -6.316e-031 1.055e-022 5.770e-028 5.980e-028 2 -5.030e-013 1.575e-008 -1.520e-008 1.472e-002 6.022e-008 6.243e-008 3 -1.005e-012 6.185e-008 -5.966e-008 2.944e-002 1.171e-007 1.214e-007 4 -1.505e-012 1.365e-007 -1.317e-007 4.416e-002 1.705e-007 1.769e-007 5 -2.002e-012 2.381e-007 -2.296e-007 5.887e-002 2.206e-007 2.289e-007 6 -2.495e-012 3.648e-007 -3.517e-007 7.359e-002 2.673e-007 2.774e-007 7 -2.983e-012 5.149e-007 -4.963e-007 8.831e-002 3.106e-007 3.225e-007 8 -3.464e-012 6.867e-007 -6.618e-007 1.030e-001 3.506e-007 3.641e-007 9 -3.939e-012 8.785e-007 -8.464e-007 1.177e-001 3.873e-007 4.023e-007 10 -4.406e-012 1.088e-006 -1.049e-006 1.325e-001 4.207e-007 4.371e-007 11 -4.863e-012 1.315e-006 -1.267e-006 1.472e-001 4.508e-007 4.684e-007 12 -5.310e-012 1.556e-006 -1.499e-006 1.619e-001 4.777e-007 4.964e-007 13 -5.746e-012 1.811e-006 -1.744e-006 1.766e-001 5.015e-007 5.210e-007 14 -6.169e-012 2.077e-006 -2.000e-006 1.913e-001 5.221e-007 5.423e-007 15 -6.580e-012 2.353e-006 -2.265e-006 2.061e-001 5.396e-007 5.605e-007 16 -6.976e-012 2.637e-006 -2.539e-006 2.208e-001 5.541e-007 5.755e-007 17 -7.357e-012 2.928e-006 -2.819e-006 2.355e-001 5.658e-007 5.874e-007 18 -7.723e-012 3.224e-006 -3.104e-006 2.502e-001 5.746e-007 5.965e-007 19 -8.072e-012 3.524e-006 -3.393e-006 2.649e-001 5.808e-007 6.028e-007 20 -8.403e-012 3.826e-006 -3.685e-006 2.797e-001 5.844e-007 6.065e-007 21 -8.717e-012 4.130e-006 -3.977e-006 2.944e-001 5.856e-007 6.077e-007

With NE/NASTRAN, the results associated with mode No. 8, are:


238


Solver Result name Result description Reference value CM2 Eigen mode 1 frequency [Hz] 1.65 CM2 Eigen mode 2 frequency [Hz] 1.65 CM2 Eigen mode 3 frequency [Hz] 16.07 CM2 Eigen mode 4 frequency [Hz] 16.07 CM2 Eigen mode 5 frequency [Hz] 50.02 CM2 Eigen mode 6 frequency [Hz] 50.02 CM2 Eigen mode 7 frequency [Hz] 76.47 CM2 Eigen mode 9 frequency [Hz] 103.20 CM2 Eigen mode 10 frequency [Hz] 103.20

Comment: The difference between the reference frequency of torsion mode (mode No. 8) and the one found by Advance Design may be explained by the fact that Advance Design is using a lumped mass matrix (see the corresponding description sheet).


Result name Result description Value Error Eigen mode 1 frequency [Hz] 1.65 Hz 0.00% Eigen mode 2 frequency [Hz] 1.65 Hz 0.00% Eigen mode 3 frequency [Hz] 16.06 Hz -0.06% Eigen mode 4 frequency [Hz] 16.06 Hz -0.06% Eigen mode 5 frequency [Hz] 50 Hz -0.04% Eigen mode 6 frequency [Hz] 50 Hz -0.04% Eigen mode 7 frequency [Hz] 76.46 Hz -0.01% Eigen mode 9 frequency [Hz] 103.14 Hz -0.06% Eigen mode 10 frequency [Hz] 103.14 Hz -0.06%


239

1.78 Fixed/free slender beam with eccentric mass or inertia (01-0096SDLLB_FEM)

Test ID: 2510

Test status: Passed

1.78.1 Description Fixed/free slender beam with eccentric mass or inertia.

Tested functions: Eigen mode frequencies, straight slender beam, combined bending-torsion, plane bending, transverse bending, punctual mass.

1.78.2 Background

1.78.2.1 Model description ■ Reference: Structure Calculation Software Validation Guide, test SDLL 15/89; ■ Analysis type: modal analysis; ■ Element type: linear. ■ Tested functions: Eigen mode frequencies, straight slender beam, combined bending-torsion, plane bending,

transverse bending, punctual mass..

1.78.2.2 Problem data

Units

I. S.

Geometry

■ Outer diameter: de= 0.35 m, ■ Inner diameter: di = 0.32 m, ■ Beam length: l = 10 m, ■ Distance BC: lBC = 1 m ■ Area: A =1.57865 x 10-2 m2 ■ Inertia: Iy = Iz = 2.21899 x 10-4m4 ■ Polar inertia: Ip = 4.43798 x 10-4m4 ■ Punctual mass: mc = 1000 kg


240


■ Longitudinal elasticity modulus of AB element: E = 2.1 x 1011 Pa, ■ Density of the linear element AB: ρ = 7800 kg/m3 ■ Poisson's ratio ν=0.3(this coefficient was not specified in the AFNOR test , the value 0.3 seems to be the more

appropriate to obtain the correct frequency value of modes No. 4 and 5 with NE/NASTRAN: ■ Elastic modulus of BC element: E = 1021 Pa ■ Density of the linear element BC: ρ = 0 kg/m3

Boundary conditions

Fixed at point A, x = 0,

Loading


1.78.2.3 Reference frequencies

Reference solutions

The different eigen frequencies are determined using a finite elements model of Euler beam (slender beam).

fz + t0 = flexion x,z + torsion

fy + tr = flexion x,y + traction

Mode Units Reference 1 (fz + t0) Hz 1.636 2 (fy + tr) Hz 1.642 3 (fy + tr) Hz 13.460 4 (fz + t0) Hz 13.590 5 (fz + t0) Hz 28.900 6 (fy + tr) Hz 31.960 7 (fz + t0) Hz 61.610 1 (fz + t0) Hz 63.930

Uncertainty about the reference solutions

The uncertainty about the reference solutions: ± 1%


■ Linear element AB: Beam ■ Imposed mesh: 50 elements. ■ Linear element BC: Beam ■ Without meshing

Modal deformations


241


Solver Result name Result description Reference value CM2 Frequency Eigen mode 1 frequency (fz + t0) [Hz] 1.636 CM2 Frequency Eigen mode 2 frequency (fy + tr) [Hz] 1.642 CM2 Frequency Eigen mode 3 frequency (fy + tr) [Hz] 13.46 CM2 Frequency Eigen mode 4 frequency (fz + t0) [Hz] 13.59 CM2 Frequency Eigen mode 5 frequency (fz + t0) [Hz] 28.90 CM2 Frequency Eigen mode 6 frequency (fy + tr) [Hz] 31.96 CM2 Frequency Eigen mode 7 frequency (fz + t0) [Hz] 61.61 CM2 Frequency Eigen mode 8 frequency (fy + tr) [Hz] 63.93

Note:

fz + t0 = flexion x,z + torsion

fy + tr = flexion x,y + traction

Observation: because the mass matrix of Advance Design is condensed and not consistent, the torsion modes obtained are not taking into account the self rotation mass inertia of the beam.


242


Result name Result description Value Error Eigen mode 1 frequency [Hz] 1.64 Hz 0.24% Eigen mode 2 frequency [Hz] 1.64 Hz -0.12% Eigen mode 3 frequency [Hz] 13.45 Hz -0.07% Eigen mode 4 frequency [Hz] 13.65 Hz 0.44% Eigen mode 5 frequency [Hz] 29.72 Hz 2.76% Eigen mode 6 frequency [Hz] 31.96 Hz 0.00% Eigen mode 7 frequency [Hz] 63.09 Hz 2.35% Eigen mode 8 frequency [Hz] 63.93 Hz 0.00%


243

1.79 Double cross with hinged ends (01-0097SDLLB_FEM)

Test ID: 2511

Test status: Passed

1.79.1 Description Double cross with hinged ends.

Tested functions: Eigen frequencies, crossed beams, in plane bending.

1.79.2 Background ■ Reference: NAFEMS, FV2 test ■ Analysis type: modal analysis; ■ Tested functions: Eigen frequencies, Crossed beams, In plane bending.


Units

I. S.

Geometry

Full square section:

■ Arm length: L = 5 m ■ Dimensions: a x b = 0.125 x 0.125 ■ Area: A = 1.563 10-2 m2 ■ Inertia: IP = 3.433 x 10-5m4

Iy = Iz = 2.035 x 10-5m4


244


■ Longitudinal elastic modulus: E = 2 x 1011 Pa, ■ Density: ρ = 8000 kg/m3

Boundary conditions

■ Outer: A, B, C, D, E, F, G, H points restraint along x and y; ■ Inner: None.

Loading


1.79.2.2 Reference frequencies Mode Units Reference

1 Hz 11.336 2,3 Hz 17.709

4 to 8 Hz 17.709 9 Hz 45.345

10,11 Hz 57.390 12 to 16 Hz 57.390


■ Linear elements type: Beam ■ Imposed mesh: 4 Elements / Arms

Modal deformations


245


Solver Result name Result description Reference value CM2 Frequency Frequency of Eigen Mode 1 [Hz] 11.336 CM2 Frequency Frequency of Eigen Mode 2 [Hz] 17.709 CM2 Frequency Frequency of Eigen Mode 3 [Hz] 17.709 CM2 Frequency Frequency of Eigen Mode 4 [Hz] 17.709 CM2 Frequency Frequency of Eigen Mode 5 [Hz] 17.709 CM2 Frequency Frequency of Eigen Mode 6 [Hz] 17.709 CM2 Frequency Frequency of Eigen Mode 7 [Hz] 17.709 CM2 Frequency Frequency of Eigen Mode 8 [Hz] 17.709 CM2 Frequency Frequency of Eigen Mode 9 [Hz] 45.345 CM2 Frequency Frequency of Eigen Mode 10 [Hz] 57.390 CM2 Frequency Frequency of Eigen Mode 11 [Hz] 57.390 CM2 Frequency Frequency of Eigen Mode 12 [Hz] 57.390 CM2 Frequency Frequency of Eigen Mode 13 [Hz] 57.390 CM2 Frequency Frequency of Eigen Mode 14 [Hz] 57.390 CM2 Frequency Frequency of Eigen Mode 15 [Hz] 57.390 CM2 Frequency Frequency of Eigen Mode 16 [Hz] 57.390


Result name Result description Value Error Frequency of Eigen Mode 1 [Hz] 11.33 Hz -0.05% Frequency of Eigen Mode 2 [Hz] 17.66 Hz -0.28% Frequency of Eigen Mode 3 [Hz] 17.66 Hz -0.28% Frequency of Eigen Mode 4 [Hz] 17.69 Hz -0.11% Frequency of Eigen Mode 5 [Hz] 17.69 Hz -0.11% Frequency of Eigen Mode 6 [Hz] 17.69 Hz -0.11% Frequency of Eigen Mode 7 [Hz] 17.69 Hz -0.11% Frequency of Eigen Mode 8 [Hz] 17.69 Hz -0.11% Frequency of Eigen Mode 9 [Hz] 45.02 Hz -0.72% Frequency of Eigen Mode 10 [Hz] 56.06 Hz -2.37% Frequency of Eigen Mode 11 [Hz] 56.06 Hz -2.37% Frequency of Eigen Mode 12 [Hz] 56.34 Hz -1.86% Frequency of Eigen Mode 13 [Hz] 56.34 Hz -1.86% Frequency of Eigen Mode 14 [Hz] 56.34 Hz -1.86% Frequency of Eigen Mode 15 [Hz] 56.34 Hz -1.86% Frequency of Eigen Mode 16 [Hz] 56.34 Hz -1.86%


246

1.80 Simple supported beam in free vibration (01-0098SDLLB_FEM)

Test ID: 2512

Test status: Passed

1.80.1 Description Simple supported beam in free vibration.

Tested functions: Shear force, eigen frequencies.

1.80.2 Background ■ Reference: NAFEMS, FV5 ■ Analysis type: modal analysis; ■ Tested functions: Shear force, eigen frequencies.


Units

I. S.

Geometry

Full square section:

■ Dimensions: a x b = 2m x 2 m ■ Area: A = 4 m2 ■ Inertia: IP = 2.25 m4

Iy = Iz = 1.333 m4


■ Longitudinal elastic modulus: E = 2 x 1011 Pa, ■ Poisson's ratio: ν = 0.3. ■ Density: ρ = 8000 kg/m3


247

Boundary conditions

■ Outer: ► x = y = z = Rx = 0 at A ; ► y = z =0 at B ;

■ Inner: None.

Loading


1.80.2.2 Reference frequencies

Mode Shape Units Reference 1 Flexion Hz 42.649 2 Flexion Hz 42.649 3 Torsion Hz 77.542 4 Traction Hz 125.00 5 Flexion Hz 148.31 6 Flexion Hz 148.31 7 Torsion Hz 233.10 8 Flexion Hz 284.55 9 Flexion Hz 284.55

Comment: Due to the condensed (lumped) nature of the mass matrix of Advance Design, the frequencies values of 3 and 7 modes cannot be found by this software. The same modeling done with NE/NASTRAN gave respectively for mode 3 and 7: 77.2 and 224.1 Hz.


■ Straight elements: linear element ■ Imposed mesh: 5 meshes

Modal deformations


248


Solver Result name Result description Reference value CM2 Frequency of eigen mode 1 [Hz] 42.649 CM2 Frequency of eigen mode 2 [Hz] 42.649 CM2 Frequency of eigen mode 3 [Hz] 77.542 CM2 Frequency of eigen mode 4 [Hz] 125.00 CM2 Frequency of eigen mode 5 [Hz] 148.31 CM2 Frequency of eigen mode 6 [Hz] 148.31 CM2 Frequency of eigen mode 7 [Hz] 233.10

Comment: The torsion modes No. 3 and 7 that are calculated with NASTRAN cannot be calculated with Advance Design CM2 solver and therefore the mode No. 3 of the Advance Design analysis corresponds to mode No. 4 of the reference. The same problem in the case of No. 7 - Advance Design, that corresponds to mode No. 8 of the reference.


Result name Result description Value Error Frequency of eigen mode 1 [Hz] 43.11 Hz 1.07% Frequency of eigen mode 2 [Hz] 43.11 Hz 1.07% Frequency of eigen mode 3 [Hz] 124.49 Hz -0.41% Frequency of eigen mode 4 [Hz] 149.38 Hz 0.72% Frequency of eigen mode 5 [Hz] 149.38 Hz 0.72% Frequency of eigen mode 6 [Hz] 269.55 Hz -5.56% Frequency of eigen mode 7 [Hz] 269.55 Hz -5.56%


249

1.81 Membrane with hot point (01-0099HSLSB_FEM)

Test ID: 2513

Test status: Passed

1.81.1 Description Membrane with hot point.

Tested functions: Stresses.

1.81.2 Background ■ Reference: NAFEMS, Test T1 ■ Analysis type: static, thermo-elastic; ■ Tested functions: Stresses.


Observation: the units system of the initial NAFEMS test, defined in mm, was transposed in m for practical reasons. However, this has no influence on the results values.


250

Units

I. S.

Geometry / meshing

A quarter of the structure is modeled by incorporating the terms of symmetries.

Thickness: 1 m


■ Longitudinal elastic modulus: E = 1 x 1011 Pa, ■ Poisson's ratio: ν = 0.3, ■ Elongation coefficient α = 0.00001.

Boundary conditions

■ Outer: ► For all nodes in y = 0, uy =0; ► For all nodes in x = 0, ux =0;

■ Inner: None.

Loading

■ External: None, ■ Internal: Hot point, thermal load ΔT = 100°C;


251

1.81.3 σyy stress at point A:

Reference solution:

Reference value: σyy = 50 MPa in A


■ Planar elements: membranes, ■ 28 planar elements, ■ 39 nodes.


Solver Result name Result description Reference value CM2 syy_mid σyy in A [MPa] 50

Note: This value (50.87) is obtained with a vertical cross section through point A. The value represents σyy at the left end of the diagram.

With CM2, it is essential to display the results with the “Smooth results on planar elements” option deactivated.


Result name Result description Value Error syy_mid Sigma yy in A [MPa] 50.8666 MPa 1.70%


252

1.82 Beam on 3 supports with T/C (k = 0) (01-0100SSNLB_FEM)

Test ID: 2514

Test status: Passed

1.82.1 Description Verifies the rotation, the displacement and the moment on a beam consisting of two elements of the same length and identical characteristics with 3 T/C supports (k = 0).

1.82.2 Background

1.82.2.1 Model description ■ Reference: internal GRAITEC test; ■ Analysis type: static non linear; ■ Element type: linear, T/C.

Units

I. S.

Geometry

■ L = 10 m ■ Section: IPE 200, Iz = 0.00001943 m4



Boundary conditions

■ Outer: ► Support at node 1 restrained along x and y (x = 0), ► Support at node 2 restrained along y (x = 10 m), ► T/C stiffness ky = 0,

■ Inner: None.

Loading

■ External: Vertical punctual load P = -100 N at x = 5 m, ■ Internal: None.


253

1.82.2.2 References solutions ky being null, the non linear model behaves the same way as the structure without support 3.

Displacements

( )( )

( )( )

( )( )

( ) rad 000153.0Lk2EI3EI32

LkEI6PL

m 00153.0Lk2EI316

PL3v

rad 000153.0Lk2EI3EI16

LkEI3PL


LkEI2PL3

3yzz

3yz

2

3

3yz

3

3

3yzz

3yz

2

2

3yzz

3yz

2

1

=+

+−=β

=+

−=

=+

+−=β

−=+

+=β

Mz Moments

( )( )

N.m 2502

MM4

PL)m5x(M

0Lk2EI316

PLk3M

0M

1z2zz

3yz

4y

2z

1z

−=−

+==

=+

=

=


■ Linear element: S beam, automatic mesh, ■ 3 nodes, ■ 2 linear elements + 1 T/C.

Deformed shape


254

Moment diagrams


Solver Result name Result description Reference value CM2 RY Rotation Ry in node 1 [rad] 0.000153 CM2 RY Rotation Ry in node 2 [rad] -0.000153 CM2 DZ Displacement V in node 3 [m] 0.00153 CM2 RY Rotation Ry in node 3 [rad] 0.000153 CM2 My Moment M in node 1 [Nm] 0 CM2 My Moment M - middle span 1 [Nm] -250


Result name Result description Value Error RY Rotation Ry in node 1 [rad] 0.000153175 Rad 0.11% RY Rotation Ry in node 2 [rad] -0.000153175 Rad -0.11% DZ Displacement V in node 3 [m] 0.00153175 m 0.11% RY Rotation Ry in node 3 [rad] -0.000153175 Rad -0.11% My Moment M in node 1 [Nm] 5.05771e-014 N*m 0.00% My Moment M - middle span 1 [Nm] -250 N*m 0.00%


255

1.83 Beam on 3 supports with T/C (k -> infinite) (01-0101SSNLB_FEM)

Test ID: 2515

Test status: Passed

1.83.1 Description Verifies the rotation, the displacement and the moment on a beam consisting of two elements of the same length and identical characteristics with 3 T/C supports (k -> infinite).

1.83.2 Background


Units

I. S.

Geometry




Boundary conditions

■ Outer: ► Support at node 1 restrained along x and y (x = 0), ► Support at node 2 restrained along y (x = 10 m), ► T/C stiffness ky → ∞ (1.1030N/m),

■ Inner: None.

Loading



256

1.83.2.2 References solutions ky being infinite, the non linear model behaves the same way as a beam on 3 supports.

Displacements

( )( )

( )( )

( )( )

( ) rad 000038.0Lk2EI3EI32

LkEI6PL

0Lk2EI316

PL3v


LkEI3PL


LkEI2PL3

3yzz

3yz

2

3

3yz

3

3

3yzz

3yz

2

2

3yzz

3yz

2

1

−=+

+−=β

=+

−=

=+

+−=β

−=+

+=β

Mz Moments

( )( )

N.m 13.2032

MM4

PL)m5x(M

N.m 75.93Lk2EI316

PLk3M

0M

1z2zz

3yz

4y

2z

1z

−=−

+==

−=+

=

=



Deformed shape


257

Moment diagram


Solver Result name Result description Reference value CM2 RY Rotation Ry - node 1 [rad] 0.000115 CM2 RY Rotation Ry - node 2 [rad] -0.000077 CM2 DZ Displacement - node 3 [m] 0 CM2 RY Rotation Ry - node 3 [rad] 0.000038 CM2 My Moment M - node 1 [Nm] 0 CM2 My Moment M - node 2 [Nm] 93.75 CM2 My Moment M - middle span 1 [Nm] -203.13


Result name

Result description Value Error

RY Rotation Ry in node 1 [rad] 0.000115005 Rad 0.00% RY Rotation Ry in node 2 [rad] -7.65875e-005 Rad 0.54% DZ Displacement - node 3 [m] 9.36486e-030 m 0.00% RY Rotation Ry in node 3 [rad] 3.81695e-005 Rad 0.44% My Moment M - node 1 [Nm] 1.3145e-013 N*m 0.00% My Moment M - node 2 [Nm] 93.6486 N*m -0.11% My Moment M - middle span 1 [Nm] -203.176 N*m -0.02%


258

1.84 Beam on 3 supports with T/C (k = -10000 N/m) (01-0102SSNLB_FEM)

Test ID: 2516

Test status: Passed

1.84.1 Description Verifies the rotation, the displacement and the moment on a beam consisting of two elements of the same length and identical characteristics with 3 T/C supports (k = -10000 N/m).

1.84.2 Background


Units

I. S.

Geometry




Boundary conditions

■ Outer: ► Support at node 1 restrained along x and y (x = 0), ► Support at node 2 restrained along y (x = 10 m), ► T/C ky Rigidity = -10000 N/m (the – sign corresponds to an upwards restraint),

■ Inner: None.

Loading



259

1.84.2.2 References solutions

Displacements

( )( )

( )( )

( )( )

( ) rad 000034.0Lk2EI3EI32

LkEI6PL

m 00058.0Lk2EI316

PL3v


LkEI3PL


LkEI2PL3

3yzz

3yz

2

3

3yz

3

3

3yzz

3yz

2

2

3yzz

3yz

2

1

=+

+−=β

=+

−=

=+

+−=β

−=+

+=β

Mz Moments

( )( )

N.m 9.2202

MM4

PL)m5x(M

N.m 15.58Lk2EI316

PLk3M

0M

1z2zz

3yz

4y

2z

1z

−=−

+==

−=+

=

=



Deformed shape


260

Moment diagram


Solver Result name Result description Reference value CM2 RY Rotation Ry in node 1 [rad] -0.000129 CM2 RY Rotation Ry in node 2 [rad] 0.000106 CM2 DZ Displacement - node 3 [m] 0.00058 CM2 RY Rotation Ry in node 3 [rad] 0.000034 CM2 My M moment - node 1 [Nm] 0 CM2 My M moment - node 2 [Nm] -58.15 CM2 My M moment - middle span 1 [Nm] -220.9


Result name Result description Value Error RY Rotation Ry in node 1 [rad] 0.000129488 Rad 0.38% RY Rotation Ry in node 2 [rad] -0.000105646 Rad 0.34% DZ Displacement - node 3 [m] 0.000581169 m 0.20% RY Rotation Ry in node 3 [rad] -3.44295e-005 Rad -1.25% My M moment - node 1 [Nm] 1.77636e-015 N*m 0.00% My M moment - node 2 [Nm] 58.1169 N*m -0.06% My M moment - middle span 1 [Nm] -220.942 N*m -0.02%


261

1.85 Linear system of truss beams (01-0103SSLLB_FEM)

Test ID: 2517

Test status: Passed

1.85.1 Description Verifies the displacement and the normal force for a bar system containing 4 elements of the same length and 2 diagonals.

1.85.2 Background

1.85.2.1 Model description ■ Reference: internal GRAITEC test; ■ Analysis type: static linear; ■ Element type: linear, bar.

Units

I. S.

Geometry

■ L = 5 m ■ Section S = 0.005 m2


Longitudinal elastic modulus: E = 2.1 x 1011 N/m2.

Boundary conditions

■ Outer: ► Support at node 1 restrained along x and y, ► Support at node 2 restrained along x and y,

■ Inner: None.


262

Loading

■ External: Horizontal punctual load P = 50000 N at node 3, ■ Internal: None.

1.85.2.2 References solutions

Displacements

m 000108.0ES11PL5v

m 000541.0ES11PL25u

m 000129.0ES11PL6v

m 000649.0ES11PL30u

4

4

3

3

==

==

−=−

=

==

N normal forces

N 32141P11

25N N 22727P115N

N 38569P11

26N N 27272P116N

N 22727P115N 0N

4243

1323

1412

−=−===

==−=−=

===


■ Linear element: bar, without meshing, ■ 4 nodes, ■ 6 linear elements.

Deformed shape


263

Normal forces


Solver Result name Result description Reference value CM2 DX u3 displacement on Node 3 [m] 0.000649 CM2 DZ v3 displacement on Node 3 [m] -0.000129 CM2 DX u4 displacement on Node 4 [m] 0.000541 CM2 DZ v4 displacement on Node 4 [m] 0.000108 CM2 Fx N12 normal force on Element 1 [N] 0 CM2 Fx N23 normal force on Element 2 [N] -27272 CM2 Fx N43 normal force on Element 3 [N] 22727 CM2 Fx N14 normal force on Element 4 [N] 22727 CM2 Fx N13 normal effort on Element 5 [N] 38569 CM2 Fx N42 normal force on Element 6 [N] -32141


Result name Result description Value Error DX u3 displacement on Node 3 [m] 0.000649287 m 0.04% DZ v3 displacement on Node 3 [m] -0.000129871 m -0.67% DX u4 displacement on Node 4 [m] 0.000541063 m 0.01% DZ v4 displacement on Node 4 [m] 0.000108224 m 0.21% Fx N12 normal force on Element 1 [N] 0 N 0.00% Fx N23 normal force on Element 2 [N] -27272.9 N 0.00% Fx N43 normal force on Element 3 [N] 22727.1 N 0.00% Fx N14 normal force on Element 4 [N] 22727.1 N 0.00% Fx N13 normal effort on Element 5 [N] 38569.8 N 0.00% Fx N42 normal force on Element 6 [N] -32140.9 N 0.00%


264

1.86 Non linear system of truss beams (01-0104SSNLB_FEM)

Test ID: 2518

Test status: Passed

1.86.1 Description Verifies the displacement and the normal force for a bar system containing 4 elements of the same length and 2 diagonals.

1.86.2 Background

1.86.2.1 Model description ■ Reference: internal GRAITEC test; ■ Analysis type: static non linear; ■ Element type: linear, bar, tie.

Units

I. S.

Geometry

■ L = 5 m ■ Section S = 0.005 m2


Longitudinal elastic modulus: E = 2.1 x 1011 N/m2.

Boundary conditions

■ Outer: ► Support at node 1 restrained along x and y, ► Support at node 2 restrained along x and y,

■ Inner: None.


265

Loading

■ External: Horizontal punctual load P = 50000 N at node 3, ■ Internal: None.

1.86.2.2 References solutions In non linear analysis without large displacement, the introduction of ties for the diagonal bars removes bar 5 (test No. 0103SSLLB_FEM allows finding an compression force in this bar at the linear calculation).

Displacements

0v

m 000238.0ESPLv

m 001195.0ES11PL5uu

4

3

43

=

−=−=

===

N normal forces

0N 0NN 70711P2N N 50000PN

0N 0N

4243

1323

1412

==

==−=−=

==


■ Linear element: bar, without meshing, ■ 4 nodes, ■ 6 linear elements.

Deformed shape


266

Normal forces


Solver Result name Result description Reference value CM2 DX u3 displacement on Node 3 [m] 0.001195 CM2 DZ v3 displacement on Node 3 [m] -0.000238 CM2 DX u4 displacement on Node 4 [m] 0.001195 CM2 DZ v4 displacement on Node 4 [m] 0 CM2 Fx N12 normal force on Element 1 [N] 0 CM2 Fx N23 normal force on Element 2 [N] -50000 CM2 Fx N34 normal force on Element 3 [N] 0 CM2 Fx N14 normal force on Element 4 [N] 0 CM2 Fx N13 normal effort on Element 5 [N] 70711 CM2 Fx N24 normal force on Element 6 [N] 0


267


Result name Result description Value Error DX u3 displacement on Node 3 [m] 0.00119035 m -0.39% DZ v3 displacement on Node 3 [m] -0.000238095 m -0.04% DX u4 displacement on Node 4 [m] 0.00119035 m -0.39% DZ v4 displacement on Node 4 [m] 9.94686e-316 m 0.00% Fx N12 normal force on Element 1 [N] 0 N 0.00% Fx N23 normal force on Element 2 [N] -50000 N 0.00% Fx N34 normal force on Element 3 [N] 0 N 0.00% Fx N14 normal force on Element 4 [N] 2.08884e-307 N 0.00% Fx N13 normal effort on Element 5 [N] 70710.7 N 0.00% Fx N24 normal force on Element 6 [N] 0 N 0.00%


268

1.87 Study of a mast subjected to an earthquake (02-0112SMLLB_P92)

Test ID: 2519

Test status: Passed

1.87.1 Description A structure consisting of 2 beams and 2 punctual masses, subjected to a lateral earthquake along X. The frequency modes, the eigen vectors, the participation factors, the displacement at the top of the mast and the forces at the top of the mast are verified.

1.87.1.1 Model description ■ Reference: internal GRAITEC test; ■ Analysis type: modal and spectral analyses; ■ Element type: linear, mass.

1.87.1.2 Material strength model

Units

I. S.

Geometry

■ Length: L = 35 m, ■ Outer radius: Rext = 3.00 m ■ Inner radius: Rint = 2.80 m

■ Axial section: S= 3.644 m2 ■ Polar inertia: Ip = 30.68 m4 ■ Bending inertias: Ix =15.34 m4

Iy = 15.34 m4

Masses

■ M1 =203873.6 kg ■ M2 =101936.8 kg


■ Longitudinal elastic modulus: E = 1.962 x 1010 N/m2, ■ Poisson's ratio: ν = 0.1, ■ Density: ρ = 25 kN/m3


269

Boundary conditions

■ Outer: Fixed in X = 0, Y = 0 m,

Loading

■ External: Seismic excitation on X direction


Linear element: beam, automatic mesh,

1.87.1.3 Seismic hypothesis in conformity with PS92 regulation ■ Zone: Nice Sophia Antipolis (Zone II). ■ Site: S1 (Medium soil, 10m thickness). ■ Construction type class: B ■ Behavior coefficient: 3 ■ Material damping: 4% (Reinforced concrete).

1.87.1.4 Modal analysis

Eigen periods reference solution

Substract the value of structure’s specific horizontal periods by solving the following equation:

( ) 0MKdet 2 =ω−

⎟⎟⎠

⎞⎜⎜⎝

⎛≡

⎟⎟⎠

⎞⎜⎜⎝

⎛−

−≡

2

1

3

M00M

M

25516

L7EI48K

Eigen modes Units Reference 1 Hz 2.085 2 Hz 10.742


270

Modal vectors

For ω1:

⎟⎟⎠

⎞⎜⎜⎝

⎛=⎟⎟

⎠

⎞⎜⎜⎝

⎛χ⇒=⎟⎟

⎠

⎞⎜⎜⎝

⎛⎟⎟⎠

⎞⎜⎜⎝

⎛⎟⎟⎠

⎞⎜⎜⎝

⎛

ωω

−⎟⎟⎠

⎞⎜⎜⎝

⎛−

−055.31

UU

0UU

M00M

25516

L7EI48

2

11

2

1

12

2

211

3

For ω2:

⎟⎟⎠

⎞⎜⎜⎝

⎛−

=⎟⎟⎠

⎞⎜⎜⎝

⎛χ

655.01

UU

2

12

Normalizing relative to the mass

⎟⎟⎠

⎞⎜⎜⎝

⎛

××

χ−

−

3

4

1 10842.210305.9

; ⎟⎟⎠

⎞⎜⎜⎝

⎛

×−×

χ−

−

3

3

2 10316.11001.2

Modal deformations


271

1.87.1.5 Spectral study

Design spectrum

Nominal acceleration:

2n1 sm5411.5a 2.085Hzf =⇒=

2n2 sm25.6aHz742.01f =⇒=

Observation: the gap between pulses is greater than 10%, so the modal responses can be regarded as independent.

Reference participation factors

Δχ=γ Mii

séismedudirectionladedirecteurVecteur: ⋅⋅⋅⋅⋅⋅Δ

Eigen modes Reference 1 479.427 2 275.609


272

Pseudo-acceleration

iiii a χ×γ×ξ×=Γ in (m/s2)

4.0%5

⎟⎟⎠

⎞⎜⎜⎝

⎛η

=ξ : Damping correction factor.

η: Structure damping.

⎟⎟⎠

⎞⎜⎜⎝

⎛=Γ

8.25562.7026

1 ⎟⎟⎠

⎞⎜⎜⎝

⎛=Γ

2.4783-3.7852

1

Reference modal displacement

⎟⎟⎠

⎞⎜⎜⎝

⎛−−

=ψ024.814E021.576E

1 ⎟⎟⎠

⎞⎜⎜⎝

⎛−

−=ψ

045.446E-048.318E

2

Equivalent static forces

⎟⎟⎠

⎞⎜⎜⎝

⎛++

=058.415E055.510E

F1 ⎟⎟⎠

⎞⎜⎜⎝

⎛+

+=

052.526E-057.717E

F2

Displacement at the top of the mast

( ) ( )( )221 04E446.502E81.4U −−+−=

Units Reference m 4.814 E-02

Shear force at the top of the mast

( ) ( )( )3

05E526.205E415.8T

22

1+−++

=

3: Being the behavior coefficient of forces

Units Reference N 2.929 E+05

Moment at the base

Units Reference N.m 1.578 E+07


Reference

Solver Result name Result description Reference value CM2 Frequency Frequency Mode 1 [Hz] 2.085 CM2 Frequency Frequency Mode 2 [Hz] 10.742 CM2 D Displacement at the top of the mast [cm] 4.814 CM2 Fz Forces at the top of the mast [N] 2.929E+05


273


Result name Result description Value Error Frequency Mode 1 [Hz] 2.08 Hz -0.24% Frequency Mode 2 [Hz] 10.74 Hz -0.02% D Displacement at the top of the mast [cm] 4.81159 cm -0.05% Fz Forces at the top of the mast [N] 292677 N -0.08%


274

1.88 Linear element in simple bending - without compressed reinforcement (02-0162SSLLB_B91)

Test ID: 2521

Test status: Passed

1.88.1 Description Verifies the reinforcement results for a concrete beam with 8 isostatic spans subjected to uniform loads.

1.88.1.1 Model description ■ Reference: J. Perchat (CHEC) reinforced concrete course ■ Analysis type: static linear; ■ Element type: planar.

Units

■ Forces: kN ■ Moment: kN.m ■ Stresses: MPa ■ Reinforcement density: cm2

Geometry

■ Beam dimensions: 0.2 x 0.5 ht ■ Length: l = 42 m in 7 spans of 6m,


■ Longitudinal elastic modulus: E = 20000 MPa, ■ Poisson's ratio: ν = 0.

Boundary conditions

■ Outer: ► Hinged at end x = 0, ► Vertical support at the same level with all other supports

■ Inner: Hinge z at each beam end (isostatic)

Loading

■ External: ► Case 1 (DL):uniform linear load g = -5 kN/m (on all spans except 8)

► Case 2 to 8 (LL):uniform linear load q = -9 kN/m (on spans 1, 3 to 7)

uniform linear load q = -15 kN/m (on span 2)

► Case 9 (ACC): uniform linear load a = -25 kN/m (on 8th span)

► Case 10 (DL):uniform linear load g = -5 kN/m (on 8th span)

Comb BAELUS: 1.35xDL+1.5xLL with duration of more than 24h (comb 101, 104 to 107)

Comb BAEULI: 1.35xDL+1.5xLL with duration between 1h and 24h (comb 102)

Comb BAELUC: 1.35xDL + 1.5xLL with duration of less than 1h (comb 103)

Comb BAELS: 1xDL + 1*LL (comb 108 to 114)

Comb BAELUA: 1xDL + 1xACC (comb 115)

■ Internal: None.


275

Reinforced concrete calculation hypothesis:

■ All concrete covers are set to 5 cm ■ BAEL 91 calculation with the revised version 99

Span Concrete Reinforcement Application Concrete Cracking 1 B20 HA fe500 D>24h No Non

prejudicial 2 B35 Adx fe235 1h<D<24h No Non

prejudicial 3 B50 HA fe 400 D<1h Yes Non

prejudicial 4 B25 HA fe500 D>24h Yes Prejudicial 5 B60 HA fe500 D>24h No Very

prejudicial 6 B30 Adx fe235 D>24h Yes Prejudicial 7 B40 HA fe500 D>24h Yes 160 MPa 8 B45 HA fe500 D<1h Yes Non

prejudicial

1.88.1.2 Reinforcement calculation

Reference solution

Span 1 Span 2 Span 3 Span 4 Span 5 Span 6 Span 7 Span 8 fc28 20 35 50 25 60 30 40 45 ft28 1.8 2.7 3.6 2.1 4.2 2.4 3 3.3 fe 500 235 400 500 500 235 500 500

teta 1 0.9 0.85 1 1 1 1 0.85 gamb 1.5 1.5 1.5 1.5 1.5 1.5 1.5 1.15 gams 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1

h 1.6 1 1.6 1.6 1.6 1 1.6 1.6

fbu 11.33 22.04 33.33 14.17 34.00 17.00 22.67 39.13 fed 434.78 204.35 347.83 434.78 434.78 204.35 434.78 500.00

sigpreju 250.00 156.67 264.00 250.00 285.15 156.67 160.00 252.76 sigtpreju 200.00 125.33 211.20 200.00 228.12 125.33 160.00 202.21

g 5.00 5.00 5.00 5.00 5.00 5.00 5.00 5.00 q 9.00 15.00 9.00 9.00 9.00 9.00 9.00 25.00

pu 20.25 29.25 20.25 20.25 20.25 20.25 20.25 30.00 pser 14.00 20.00 14.00 14.00 14.00 14.00 14.00

l 6.00 6.00 6.00 6.00 6.00 6.00 6.00 6.00 Mu 91.13 131.63 91.13 91.13 91.13 91.13 91.13 135.00

Mser 63.00 90.00 63.00 63.00 63.00 63.00 63.00 Vu 60.75 87.75 60.75 60.75 60.75 60.75 60.75 90.00

Longitudinal reinforcement calculation according to ELU ubu 0.199 0.147 0.068 0.159 0.066 0.132 0.099 0.085 a 0.279 0.200 0.087 0.217 0.086 0.178 0.131 0.111 z 0.400 0.414 0.434 0.411 0.435 0.418 0.426 0.430

Au 5.24 15.56 6.03 5.10 4.82 10.67 4.91 6.28 Main reinforcement calculation with prejudicial cracking according to SLS

A 1.000 1.000 1.000 1.000 1.000 1.000 1.000 1.000 B -3.000 -3.000 -3.000 -3.000 -3.000 -3.000 -3.000 -3.000 C -0.56000 -0.89362 -0.87500 D 0.56000 0.89362 0.87500

alpha1 0.367 0.442 0.438 z 0.395 0.384 0.384

Aserp 6.38 10.48 10.25


276

Main reinforcement calculation with very prejudicial cracking according to SLS A 1.00 1.00 1.00 1.00 1.00 1.00 1.00 1.00 B -3.00 -3.00 -3.00 -3.00 -3.00 -3.00 -3.00 -3.00 C -0.70 -1.60 -0.66 -0.70 -0.61371 -1.12 -0.88 0.00 D 0.70 1.60 0.66 0.70 0.61371 1.12 0.88 0.00

alpha1 0.381 z 0.393

Asertp 7.030 Transversal reinforcement calculation

tu 0.68 0.98 0.68 0.68 0.68 0.68 0.68 1.00 k 1.00 1.00 0.00 0.00 0.00 0.00 0.00 0.00

At/st 0.69 1.79 4.31 3.45 3.45 7.34 3.45 4.44 Recapitulation

Aflex 5.24 15.56 6.03 6.38 7.03 10.67 10.25 6.28 Aminflex 0.75 2.38 1.86 0.87 1.74 2.11 1.24 1.37

At 0.69 1.79 4.31 3.45 3.45 7.34 3.45 4.44 Atmin 1.60 3.40 2.00 1.60 1.60 3.40 1.60 1.60


■ Linear elements: beams with imposed mesh ■ 29 nodes, ■ 28 linear elements.


Reference

Solver Result name Result description Reference value CM2 Az Inf. main reinf. T1 [cm2] 5.24 CM2 Amin Min. main reinf. T1 [cm2] 0.75 CM2 Atz Trans. reinf. T1 [cm2] 0.69 CM2 Az Inf. main reinf. T2 [cm2] 15.56 CM2 Amin Min. main reinf. T2 [cm2] 2.38 CM2 Atz Trans. reinf. T2 [cm2] 1.79 CM2 Az Inf. main reinf. T3 [cm2] 6.03 CM2 Amin Min. main reinf. T3 [cm2] 1.86 CM2 Atz Trans. reinf. T3 [cm2] 4.31 CM2 Az Inf. main reinf. T4 [cm2] 6.38 CM2 Amin Min. main reinf. T4 [cm2] 0.87 CM2 Atz Trans. reinf. T4 [cm2] 3.45 CM2 Az Inf. main reinf. T5 [cm2] 7.03 CM2 Amin Min. main reinf. T5 [cm2] 1.74 CM2 Atz Trans. reinf. T5 [cm2] 3.45 CM2 Az Inf. main reinf. T6 [cm2] 10.67 CM2 Amin Min. main reinf. T6 [cm2] 2.11 CM2 Atz Trans. reinf. T6 [cm2] 7.34 CM2 Az Inf. main reinf. T7 [cm2] 10.25 CM2 Amin Min. main. reinf. T7 [cm2] 1.24 CM2 Atz Trans. reinf. T7 [cm2] 3.45 CM2 Az Inf. main reinf. T8 [cm2] 6.28 CM2 Amin Min. main reinf. T8 [cm2] 1.37 CM2 Atz Trans. reinf. T8 [cm2] 4.44

The "Mu limit" method must be applied to attain the same results.


277


Result name Result description Value Error Az Inf. main reinf. T1 [cm²] -5.24348 cm² -0.07% Amin Min. main reinf. T1 [cm²] 0.7452 cm² -0.64% Atz Trans. reinf. T1 [cm²] 0.69 cm² 0.00% Az Inf. main reinf. T2 [cm²] -15.5613 cm² -0.01% Amin Min. main reinf. T2 [cm²] 2.3783 cm² -0.07% Atz Trans. reinf. T2 [cm²] 1.79433 cm² 0.24% Az Inf. main reinf. T3 [cm²] -6.03286 cm² -0.05% Amin Min. main reinf. T3 [cm²] 1.863 cm² 0.16% Atz Trans. reinf. T3 [cm²] 4.3125 cm² 0.06% Az Inf. main reinf. T4 [cm²] -6.38336 cm² -0.05% Amin Min. main reinf. T4 [cm²] 0.8694 cm² -0.07% Atz Trans. reinf. T4 [cm²] 3.45 cm² 0.00% Az Inf. main reinf. T5 [cm²] -7.03527 cm² -0.07% Amin Min. main reinf. T5 [cm²] 1.7388 cm² -0.07% Atz Trans. reinf. T5 [cm²] 3.45 cm² 0.00% Az Inf. main reinf. T6 [cm²] -10.6698 cm² 0.00% Amin Min. main reinf. T6 [cm²] 2.11404 cm² 0.19% Atz Trans. reinf. T6 [cm²] 7.34043 cm² 0.01% Az Inf. main reinf. T7 [cm²] -10.2733 cm² -0.23% Amin Min. main. reinf. T7 [cm²] 1.242 cm² 0.16% Atz Trans. reinf. T7 [cm²] 3.45 cm² 0.00% Az Inf. main reinf. T8 [cm²] -6.29338 cm² -0.21% Amin Min. main reinf. T8 [cm²] 1.3662 cm² -0.28% Atz Trans. reinf. T8 [cm²] 4.44444 cm² 0.10%


278

1.89 Design of a Steel Structure according to CM66 (03-0206SSLLG_CM66)

Test ID: 2522

Test status: Passed

1.89.1 Description Verifies the steel calculation results (maximum displacement, normal force, bending moment, deflections, buckling lengths, lateral-torsional buckling and cross section optimization) for a simple metallic framework with a concrete floor, according to CM66.

1.89.2 Background

1.89.2.1 Model description ■ Calculation model: Simple metallic framework with a concrete floor. ■ Load case:

► Permanent loads: 150 kg/m² for the floor and 25kg/m² for the roof. ► Overloads: 250 kg/m² on the floor. ► Wind loads on region II for a normal location ► Snow loads on region 2B at an altitude of 750m.

■ CM66 Combinations

Model preview


279

Structure’s load case Code No. Type Title CMP 1 Static SW + Dead loads CMS 2 Static Overloads for usage CMV 3 Static Wind overloads along +X in overpressure CMV 4 Static Wind overloads along +X in depression CMV 5 Static Wind overloads along -X in overpressure CMV 6 Static Wind overloads along -X in depression CMV 7 Static Wind overloads along +Z in overpressure CMV 8 Static Wind overloads along +Z in depression CMV 9 Static Wind overloads along -Z in overpressure CMV 10 Static Wind overloads along -Z in depression CMN 11 Static Normal snow overloads

1.89.2.2 Effel Structure results Displacement Envelope (“CMCD" load combinations)

Envelope of linear element forces D DX DY DZ Env. Case No. Max.

location (cm) (cm) (cm) (cm) Max(D) 213 148 CENTER 12.115 0.037 12.035 -1.393 Min(D) 188 1.1 START 0.000 0.000 0.000 0.000

Max(DX) 204 72.1 START 3.138 3.099 0.434 0.244 Min(DX) 204 313 END 2.872 -1.872 -0.129 -2.174 Max(DY) 213 148 CENTER 12.115 0.037 12.035 -1.393 Min(DY) 213 61.5 END 9.986 -0.118 -9.985 0.046 Max(DZ) 201 371 CENTER 4.149 -0.006 -0.188 4.145 Min(DZ) 203 370 CENTER 4.124 -0.006 -0.240 -4.118

Envelope of forces on linear elements (“CMCFN” load combinations)

Envelope of linear element forces Fx Fy Fz Mx My Mz Env. Case No. MaxSite (T) (T) (T) (T*m) (T*m) (T*m)

Max (Fx) 120 4.1 START 19.423 -4.108 -1.384 -0.003 1.505 7.551 Min (Fx) 138 98 START -41.618 -0.962 -0.192 0.000 0.000 0.000 Max(Fy) 120 57 END -13.473 16.349 -0.016 -0.003 0.002 55.744 Min(Fy) 120 60 START -15.994 -16.112 -0.006 -3E-004 6E-006 53.096 Max(Fz) 177 371 START -3.486 -0.118 2.655 0.000 0.000 0.000 Min(Fz) 187 370 START -3.666 -0.147 -2.658 0.000 0.000 0.000 Max(Mx) 120 111 END 3.933 4.840 0.278 0.028 -4E-005 11.531 Min(Mx) 120 21 END -22.324 13.785 -0.191 -0.028 -0.004 42.562 Max(My) 177 371 CENTER -3.099 -0.118 -0.323 0.000 4.403 -0.500 Min(My) 179 370 CENTER -3.283 -0.155 0.321 0.000 -4.373 -0.660 Max (Mz) 120 57 END -13.473 16.349 -0.016 -0.003 0.002 55.744 Min (Mz) 120 59.2 END -19.455 -8.969 -0.702 -0.003 -0.001 -57.105 Envelope of linear element stresses (“CMCFN” load combinations)

Envelope of linear element stresses sxxMax sxyMax sxzMax sFxx sMxxMax Env. Case No. MaxSite (MPa) (MPa) (MPa) (MPa) (MPa)

Max(sxxMax) 120 59.2 END 273.860 -14.696 -1.024 -16.453 290.312 Min(sxxMax) 120 292 START -150.743 0.000 0.000 -150.743 0.000 Max(sxyMax) 120 57 START 262.954 37.139 -0.030 -15.609 278.562 Min(sxyMax) 120 60 END 241.643 -36.595 -0.011 -18.536 260.179 Max(sxzMax) 185 371 START -2.949 -0.183 3.876 -2.949 0.000 Min(sxzMax) 179 370 START -3.104 -0.255 -3.882 -3.104 0.000 Max(sFxx) 120 293 END 161.095 9E-005 -0.002 161.095 0.000 Min(sFxx) 120 292 START -150.743 0.000 0.000 -150.743 0.000

Max(sMxxMax) 120 59.2 END 273.860 -14.696 -1.024 -16.453 290.312 Min(sMxxMax) 1 1.1 START -4.511 3.155 -0.646 -4.511 0.000


280

1.89.2.3 CM66 Effel Expertise results

Hypotheses

For columns

■ Deflections: 1/150 Envelopes deflections calculation.

■ Buckling XY plane: Automatic calculation of the structure on displaceable nodes XZ plane: Automatic calculation of the structure on fixed nodes

■ Lateral-torsional buckling: Ldi automatic calculation: hinged restraint Lds automatic calculation: hinged restraint

For rafters


■ Buckling: XY plane: Automatic calculation of the structure on displaceable nodes XZ plane: Automatic calculation of the structure on fixed nodes

■ Lateral-torsional buckling: Ldi automatic calculation: no restraint Lds automatic calculation: hinged restraint

For columns


■ Buckling: XY plane: Automatic calculation of the structure on displaceable nodes XZ plane: Automatic calculation of the structure on displaceable nodes

■ Lateral-torsional buckling: Ldi automatic calculation: hinged restraint Lds automatic calculation: hinged restraint

Optimization parameters

■ Work ratio optimization between 90 and 100% ■ All the sections from the library are available. ■ Labels optimization.

The results of the optimization given below correspond to an iteration of the finite elements calculation.

Deflection verification

Ratio


281

Max values on the element

■ Columns: L / 168 ■ Rafter: L / 96 ■ Column: L / 924

CM Stress diagrams

Work ratio

Stresses


282

Max values on the element ■ Columns: 375.16 MPa ■ Rafter: 339.79 MPa ■ Column: 180.98 MPa

Buckling lengths

Lfy

Lfz


283

Lateral-torsional buckling lengths

Ldi

Lds


284

Optimization


Solver Result name Result description Reference value CM2 D Maximum displacement (CMCD) [cm] 12.115 CM2 Fx Envelope normal force (CMCFN) Min (Fx) [T] -41.618 CM2 Fx Envelope normal force (CMCFN) Max (Fx) [T] 19.423 CM2 My Envelope bending moment (CMCFN) Min (Mz) [Tm] -57.105 CM2 My Envelope bending moment (CMCFN) Max (Mz) [Tm] 55.744

Warning, the Mz bending moment of Effel Structure corresponds to the My bending moment of Advance Design.

Solver Result name Result description Reference value CM2 Deflection CM deflections on Columns [adm] L / 168 (89%) CM2 Deflection CM deflections on Rafters [adm] L / 96 (208%) CM2 Deflection CM deflections on Columns [adm] L / 924 (16%) CM2 Stress CM stresses on Columns [MPa] 374.67 CM2 Stress CM stresses on Rafters [MPa] 339.74 CM2 Stress CM stresses on Columns [MPa] 180.98 CM2 Lfy Buckling lengths on Columns Lfy [m] 8.02 CM2 Lfz Buckling lengths on Columns Lfz [m] 24.07 CM2 Lfy Buckling lengths on Rafters Lfy [m] 1.72 CM2 Lfz Buckling lengths on Rafters Lfz [m] 20.25 CM2C Lfy Buckling lengths on Columns Lfy [m] 4.20 CM2 Lfz Buckling lengths on Columns Lfz [m] 5.67


285

Warning, the local axes in Effel Structure are opposite to those in Advance Design.

Solver Result name Result description Reference value CM2 Ldi Lateral-torsional buckling lengths on Columns Ldi [m] 8.5 CM2 Lds Lateral-torsional buckling lengths on Columns Lds [m] 8.5 CM2 Ldi Lateral-torsional buckling lengths on Rafters Ldi [m] 8.61 CM2 Lds Lateral-torsional buckling lengths on Rafters Lds [m] 1.72 CM2 Ldi Lateral-torsional buckling lengths on Columns Ldi [m] 2 CM2 Lds Lateral-torsional buckling lengths on Columns Lds [m] 2

Solver Result name Result description Rate (%) Final section CM2 Work ratio IPE500 columns - section optimization [adm] 1.59 IPE600 CM2 Work ratio IPE400 rafters - section optimization [adm] 1.45 IPE500 CM2 Work ratio IPE400 columns - section optimization [adm] 0.77 IPE360


Result name Result description Value Error D Maximum displacement (CMCD) [cm] 12.1382 cm 0.19% Fx Envelope normal force (CMCFN) Min (Fx) [T] -41.6549 T -0.09% Fx Envelope normal force (CMCFN) Max (Fx) [T] 19.4882 T 0.33% My Envelope bending moment (CMCFN) Min (Mz)[Tm] -57.1211 T*m -0.03% My Envelope bending moment (CMCFN) Max (Mz) [Tm] 55.7711 T*m 0.05% Deflection CM deflections on Columns [adm] 167.676 Adim. -0.19% Deflection CM deflections on Rafters [adm] 96.105 Adim. 0.11% Deflection CM deflections on Columns [adm] 925.321 Adim. 0.14% Stress CM stresses on Columns [MPa] 374.631 MPa -0.01% Stress CM stresses on Rafters [MPa] 352.399 MPa 3.59% Stress CM stresses on Columns [MPa] 180.674 MPa -0.17% Lfy Buckling lengths on Columns Lfy [m] 7.96711 m -0.66% Lfz Buckling lengths on Columns Lfz [m] 24.0693 m 0.00% Lfy Buckling lengths on Rafters Lfy [m] 6.63415 m 0.06% Lfz Buckling lengths on Rafters Lfz [m] 20.2452 m -0.02% Lfy Buckling lengths on Columns Lfy [m] 4.19567 m -0.10% Lfz Buckling lengths on Columns Lfz [m] 5.67211 m 0.04% Ldi Lateral-torsional buckling lengths on Columns Ldi [m] 8.5 m 0.00% Lds Lateral-torsional buckling lengths on Columns Lds [m] 8.5 m 0.00% Ldi Lateral-torsional buckling lengths on Rafters Ldi [m] 8.61187 m 0.02% Lds Lateral-torsional buckling lengths on Rafters Lds [m] 8.61187 m 0.02% Ldi Lateral-torsional buckling lengths on Columns Ldi [m] 2 m 0.00% Lds Lateral-torsional buckling lengths on Columns Lds [m] 2 m 0.00% Work ratio IPE500 columns - section optimization [adm] 1.59418 Adim. 0.26% Work ratio IPE400 rafters - section optimization [adm] 1.49957 Adim. 3.31% Work ratio IPE400 columns - section optimization [adm] 0.768826 Adim. -0.15%


286

1.90 Design of a 2D portal frame (03-0207SSLLG_CM66)

Test ID: 2523

Test status: Passed

1.90.1 Description Verifies the steel calculation results (displacement at ridge, normal forces, bending moments, deflections, stresses, buckling lengths, lateral torsional buckling lengths and cross section optimization) for a 2D metallic portal frame, according to CM66.

1.90.2 Background

1.90.2.1 Model description ■ Calculation model: 2D metallic portal frame.

► Column section: IPE500 ► Rafter section: IPE400 ► Base plates: hinged. ► Portal frame width: 20m ► Columns height: 6m ► Portal frame height at the ridge: 7.5m

■ Load case: ► Permanent loads: 150 kg/m on the roof + elements self weight. ► Usage overloads: 800 kg/ml on the roof

■ Mesh density: 1m

Model preview

Combinations

Code Numbers Type Title CMP 1 Static Permanent load + self weight CMS 2 Static Usage overloads

CMCFN 101 Comb_Lin 1.333P CMCFN 102 Comb_Lin 1.333P+1.5S CMCFN 103 Comb_Lin P+1.5S CMCD 104 Comb_Lin P+S


287

1.90.2.2 Effel Structure Results

Ridge displacements (combination 104)

Diagram of normal force envelope


288

Envelope of bending moments diagram

1.90.2.3 Effel Expert CM results

Main hypotheses

For columns


■ Buckling: XY plane: Automatic calculation of the structure on fixed nodes XZ plane: Automatic calculation of the structure on fixed nodes

Ka-Kb Method

■ Lateral-torsional buckling: Ldi automatic calculation: no restraints Lds imposed value: 2 m

For the rafters


■ Buckling: XY plane: Automatic calculation of the structure on fixed nodes XZ plane: Automatic calculation of the structure on fixed nodes

Ka-Kb Method

■ Lateral-torsional buckling: Ldi automatic calculation: No restraints Lds imposed value: 1.5m

Optimization criteria

■ Work ratio optimization between 90 and 100% ■ Labels optimization (on Advance Design templates)


289

Deflection verification

Ratio

CM Stress diagrams

Work ratio

Stresses


290

Buckling lengths

Lfy

Lfz

Lateral-torsional buckling lengths

Ldi


291

Lds

Optimization


Solver Result name Result description Reference value CM2 D Displacement at the ridge [cm] 9.36 CM2 Fx Envelope normal forces on Columns (min) [T] -15.77 CM2 Fx Envelope normal forces on Rafters (max) [T] -1.02 CM2 My Envelope bending moments on Columns (min) [T.m] -42.41 CM2 My Envelope bending moments on Rafters (max) [T.m] 42.41 CM2 Deflection CM deflections on Columns [%] L / 438 (34%) CM2 Deflection CM deflections on Rafters [%] L / 111 (180%) CM2 Stress CM stresses on Columns [MPa] 230.34 CM2 Stress CM stresses on Rafters [MPa] 458.38 CM2 Lfy Buckling lengths on Columns - Lfy [m] 5.84 CM2 Lfz Buckling lengths on Columns - Lfz [m] 6 CM2 Lfy Buckling lengths on Rafters - Lfy [m] 7.08 CM2 Lfz Buckling lengths on Rafters - Lfz [m] 10.11

Warning, the local axes in Effel Structure have different orientation in Advance Design.


292

Solver Result name Result description Reference value CM2 Ldi Lateral-torsional buckling lengths on Columns Ldi [m] 6 CM2 Lds Lateral-torsional buckling lengths on Columns Lds [m] 2 CM2 Ldi Lateral-torsional buckling lengths on Rafters Ldi [m] 10.11 CM2 Lds Lateral-torsional buckling lengths on Rafters Lds [m] 1.5

Solver Result name Result description Rate (%) Final section CM2 Work ratio IPE500 columns - section optimization 98 IPE500 CM2 Work ratio IPE400 rafters - section optimization 195 IPE550


Result name Result description Value Error D Displacement at the ridge [cm] 9.36473 cm 0.05% Fx Envelope normal forces on Columns (min) [T] -15.7798 T -0.06% Fx Envelope normal forces on Rafters (max) [T] -1.0161 T 0.38% My Envelope bending moments on Columns (min) [Tm] 42.4226 T*m 0.03% My Envelope bending moments on Rafters (max) [Tm] 42.4226 T*m 0.03% Deflection CM deflections on Columns [adm] 438.077 Adim. 0.02% Deflection CM deflections on Rafters [adm] 111.325 Adim. 0.29% Stress CM stresses on Columns [adm] 230.331 MPa 0.00% Stress CM stresses on Rafters [adm] 458.367 MPa 0.00% Lfy Buckling lengths on Columns - Lfy [m] 6 m 0.00% Lfz Buckling lengths on Columns - Lfz [m] 5.84401 m 0.07% Lfy Buckling lengths on Rafters - Lfy [m] 10.1119 m 0.02% Lfz Buckling lengths on Rafters - Lfz [m] 7.07904 m -0.01% Ldi Lateral-torsional buckling lengths on Columns Ldi [m] 6 m 0.00% Lds Lateral-torsional buckling lengths on Columns Lds [m] 2 m 0.00% Ldi Lateral-torsional buckling lengths on Rafters Ldi [m] 10.1119 m 0.02% Lds Lateral-torsional buckling lengths on Rafters Lds [m] 1.5 m 0.00% Work ratio IPE500 columns - section optimization [adm] 0.980131 Adim. 0.01% Work ratio IPE400 rafters - section optimization [adm] 1.9505 Adim. 0.03%


293

1.91 Design of a concrete floor with an opening (03-0208SSLLG_BAEL91)

Test ID: 2524

Test status: Passed

1.91.1 Description Verifies the displacements, bending moments and reinforcement results for a 2D concrete slab with supports and punctual loads.

1.91.2 Background

1.91.2.1 Model description ■ Calculation model: 2D concrete slab.

► Slab thickness: 20 cm ► Slab length: 20m ► Slab width: 10m ► The supports (punctual and linear) are considered as hinged. ► Supports positioning (see scheme below) ► 1,50m*2,50m opening => see positioning on the following scheme

■ Materials: ► Concrete B25 ► Young module: E= 36000 MPa

■ Load case: ► Permanent loads: 100 kg/m2 ► Permanent loads: 200 kg/ml around the opening ► Punctual loads of 2T in permanent loads (see the following definition) ► Usage overloads: 250 kg/m2

■ Mesh density: 0.5 m

Slab geometry


294

Support positions

Positions of punctual loads


295

Global loading overview

Load Combinations

Code Numbers Type Title BAGMAX 1 Static Permanent loads + self weight

BAQ 2 Static Usage overloads BAELS 101 Comb_Lin Gmax+Q BAELU 102 Comb_Lin 1.35Gmax+1.5Q


296

1.91.2.2 Effel Structure Results

SLS max displacements (load combination 101)

Mx bending moment for ULS load combination


297

My bending moment for ULS load combination

Mxy bending moment for ULS load combination

1.91.2.3 Effel RC Expert Results

Main hypothesis

■ Top and bottom concrete covers: 3 cm ■ Slightly dangerous cracking ■ Concrete B25 => Fc28= 25 MPa ■ Reinforcement calculation according to Wood method. ■ Calculation starting from non averaged forces.


298

Axi reinforcements

Ayi reinforcements


299

Axs reinforcements

Ays reinforcements


300


Solver

Result name

Result description Reference value

CM2 D Max displacement for SLS (load combination 101) [cm] 0.176 CM2 Myy Mx and My bending moments for ULS (load combination 102) Max(Mx) [kN.m] 25.20 CM2 Myy Mx and My bending moments for ULS (load combination 102) Min(Mx) [kN.m] -15.71 CM2 Mxx Mx and My bending moments for ULS (load combination 102) Max(My) [kN.m] 31.17 CM2 Mxx Mx and My bending moments for ULS (load combination 102) Min(My) [kN.m] -18.79 CM2 Mxy Mx and My bending moments for ULS (load combination 102) Max (Mxy) [kN.m] 10.26 CM2 Mxy Mx and My bending moments for ULS (load combination 102) Min (Mxy) [kN.m] -10.14 CM2 Axi Theoretic reinforcements Axi [cm2] 3.84 CM2 Axs Theoretic reinforcements Axs [cm2] 3.55 CM2 Ayi Theoretic reinforcements Ayi [cm2] 3.75 CM2 Ays Theoretic reinforcements Ays [cm2] 4.53

These values are obtained from the maximum values from the mesh.


Result name Result description Value Error D Max displacement for SLS (load combination 101) [cm] 0.174641 cm -0.78% Myy Mx and My bending moments for ULS (load combination 102)

Max(Mx) [kNm] 25.2594 kN*m 0.24%

Myy Mx and My bending moments for ULS (load combination 102) Min(Mx) [kNm]

-15.6835 kN*m 0.17%

Mxx Mx and My bending moments for ULS (load combination 102) Max(My) [kNm]

31.2449 kN*m 0.24%

Mxx Mx and My bending moments for ULS (load combination 102) Min(My) [kNm]

-18.7726 kN*m 0.09%

Mxy Mx and My bending moments for ULS (load combination 102) Max (Mxy) [kNm]

10.1558 kN*m -1.03%

Mxy Mx and My bending moments for ULS (load combination 102) Min (Mxy) [kNm]

-10.2508 kN*m -1.08%

Axi Theoretic reinforcements Axi [cm2] 3.83063 cm² -0.24% Axs Theoretic reinforcementsAxs [cm2] 3.629 cm² 2.18% Ayi Theoretic reinforcements Ayi [cm2] 3.72879 cm² -0.57% Ays Theoretic reinforcements Ays [cm2] 4.61909 cm² 1.93%


301

1.92 Verifying displacements for liniar element for vertical seism (TTAD #11756)

Test ID: 3442

Test status: Passed

1.92.1 Description Verifies the displacements results on a inclined steel bar for vertical seism according to Eurocodes 8 localization and generates the corresponding report.

The steel bar has a rigid support and IPE100 cross section and is subjected to self weight and seism load on Z direction (vertical).

1.93 Generating planar efforts before and after selecting a saved vue (TTAD #11849)

Test ID: 3454

Test status: Passed

1.93.1 Description Generates efforts for all planar elements before and after selecting the third saved vue

1.94 Verifying constraints for triangular mesh on planar element (TTAD #11447)

Test ID: 3460

Test status: Passed

1.94.1 Description Performs the finite elements calculation, verifies the stresses for triangular mesh on a planar element and generates a report for planar elements stresses in neutral fiber.

The planar element is 20 cm thick, C20/25 material with a linear rigid support. A linear load of 30.00 kN is applied on FX direction.

1.95 Verifying forces for triangular meshing on planar element (TTAD #11723)

Test ID: 3463

Test status: Passed

1.95.1 Description Performs the finite elements calculation, verifies the forces for triangular meshing on a planar element and generates a report for planar elements forces by load case.

The planar element is a square shell (5 m) with a thickness of 20 cm, C20/25 material with a linear rigid support. A linear load of -10.00 kN is applied on FZ direction.


302

1.96 Verifying stresses in beam with "extend into wall" property (TTAD #11680)

Test ID: 3491

Test status: Passed

1.96.1 Description Verifies the results on two concrete beams which have the "Extend into the wall" option enabled. One of the beams is connected to 2 walls on both sides and one with a wall and a pole. Generates the linear elements forces by elements report.

1.97 Verifying diagrams after changing the view from standard (top, left,...) to user view (TTAD #11854)

Test ID: 3539

Test status: Passed

1.97.1 Description Verifies the results diagrams display after changing the view from standard (top, left,...) to user view.

1.98 Verifying forces results on concrete linear elements (TTAD #11647)

Test ID: 3551

Test status: Passed

1.98.1 Description Verifies forces results on concrete beams consisting of a linear element and on beams consisting of two linear elements. Generates the linear elements forces by load case report.

1.99 Generating results for Torsors NZ/Group (TTAD #11633)

Test ID: 3594

Test status: Passed

1.99.1 Description Performs the finite elements calculation on a complex concrete structure with four levels. Generates results for Torsors NZ/Group. Verifies the legend results.

The structure has 88 linear elements, 30 planar elements, 48 windwalls, etc.


303

1.100 Verifying Sxx results on beams (TTAD #11599)

Test ID: 3595

Test status: Passed

1.100.1 Description Performs the finite elements calculation on a complex model with concrete, steel and timber elements. Verifies the Sxx results on beams. Generates the maximum stresses report.

The structure has 40 timber linear elements, 24 concrete linear elements, 143 steel elements. The loads applied on the structure: dead loads, live loads, snow loads, wind loads and temperature loads (according to Eurocodes).

1.101 Verifying the level mass center (TTAD #11573, TTAD #12315)

Test ID: 3609

Test status: Passed

1.101.1 Description Performs the finite elements calculation on a model with two planar concrete elements with a linear support. Verifies the level mass center and generates the "Excited total masses" and "Level modal mass and rigidity centers" reports.

The model consists of two planar concrete elements with a linear fixed support. The loads applied on the model: self weight, a planar live load of -1 kN and seism loads according to French standards of Eurocodes 8.

1.102 Verifying diagrams for Mf Torsors on divided walls (TTAD #11557)

Test ID: 3610

Test status: Passed

1.102.1 Description Performs the finite elements calculation and verifies the results diagrams for Mf torsors on a high wall divided in 6 walls (by height).

The loads applied on the model: self weight, two live load cases and seism loads according to Eurocodes 8.

1.103 Verifying results on puctual supports (TTAD #11489)

Test ID: 3693

Test status: Passed

1.103.1 Description Performs the finite elements calculation and generates the punctual supports report, containing the following tables: "Displacements of point supports by load case", "Displacements of point supports by element", "Point support actions by load case", "Point support actions by element" and "Sum of actions on supports and nodes restraints".

The structure consists of concrete, steeel and timber linear elements with punctual supports.


304

1.104 Generating a report with torsors / level (TTAD #11421)

Test ID: 3774

Test status: Passed

1.104.1 Description Generates a report with torsors / level.

1.105 Verifying nonlinear analysis results for frames with semi-rigid joints and rigid joints (TTAD #11495)

Test ID: 3795

Test status: Passed

1.105.1 Description Verifies the nonlinear analysis results for two frames with one level. One of the frames has semi-rigid joints and the other has rigid joints.

1.106 Verifying tension/compression supports on nonlinear analysis (TTAD #11518)

Test ID: 4197

Test status: Passed

1.106.1 Description Verifies the supports behaviour when the rigidity is very big.

Performs the finite elements calculation and generates the "Displacements of linear elements by element" report.

The model consists of a vertical linear element (concrete B20, R20*30 cross section) with a rigid punctual support at the base and a T/C punctual support at the top. A large value of the KTX stiffener of the T/C support is defined. Two loads of 500.00 kN are applied.

1.107 Verifying tension/compression supports on nonlinear analysis (TTAD #11518)

Test ID: 4198

Test status: Passed

1.107.1 Description Verifies the behaviour of supports with several rigidities fields defined.

Performs the finite elements calculation and generates the "Displacements of linear elements by element" report.

The model consists of a vertical linear element (concrete B20, R20*30 cross section) with a rigid punctual support at the base and a T/C punctual support at the top. A value of 15000.00 kN/m is defined for the KTX and KTZ stiffeners of the T/C support. Two loads of 500.00 kN are applied.


305

1.108 Verifying the main axes results on a planar element (TTAD #11725)

Test ID: 4310

Test status: Passed

1.108.1 Description Verifies the main axes results on a planar element.

Performs the finite elements calculation for a concrete wall (20 cm thick) with a linear support. Displays the forces results on the planar element main axes.

1.109 Verifying the display of the forces results on planar supports (TTAD #11728)

Test ID: 4375

Test status: Passed

1.109.1 Description Performs the finite elements calculation and verifies the display of the forces results on a planar support. The model consists of a concrete vertical alement with a planar support.

1.110 Verifying the internal forces results for a simple supported steel beam

Test ID: 4533

Test status: Passed

1.110.1 Description Performs the finite elements calculation for a horizontal element (S235 material and IPE180 cross section) with two hinge rigid supports at each end. One of the supports has translation restraints on X, Y and Z, the other support has restraints on Y and Z.

Verifies the internal forces My, Fz.

Validated according to:

Example: 3.1 - Simple beam bending without the stability loss

Publication: Steel structures members - Examples according to Eurocodes

By: F. Wald a kol.

1.111 Verifying forces on elastic linear support which is defined in a user workplane (TTAD #11929)

Test ID: 4553

Test status: Passed

1.111.1 Description Verifies forces on elastic linear support, which is defined in a user workplane, and generates a report with forces for linear support in global and local workplane.

2 CAD, Rendering and Visualization


308

2.1 Verifying hide/show elements command (TTAD #11753)

Test ID: 3443

Test status: Passed

2.1.1 Description Verifies the hide/show elements command for the whole structure using the right-click option.

2.2 System stability during section cut results verification (TTAD #11752)

Test ID: 3457

Test status: Passed

2.2.1 Description Performs the finite elements calculation and verifies the section cut results on a concrete planar element with an opening.

2.3 Verifying the grid text position (TTAD #11704)

Test ID: 3464

Test status: Passed

2.3.1 Description Verifies the grid text position from different views.

2.4 Verifying the grid text position (TTAD #11657)

Test ID: 3465

Test status: Passed

2.4.1 Description Verifies the grid text position from different views.

2.5 Generating combinations (TTAD #11721)

Test ID: 3468

Test status: Passed

2.5.1 Description Generates combinations for three types of loads: live loads, dead loads and snow (with an altitude > 1000 m and base effect); generates the combinations description report.


309

2.6 Verifying the coordinates system symbol (TTAD #11611)

Test ID: 3550

Test status: Passed

2.6.1 Description Verifies the coordinates system symbol display from different views.

2.7 Verifying descriptive actors after creating analysis (TTAD #11589)

Test ID: 3579

Test status: Passed

2.7.1 Description Generates the finite elements calculation on a complex concrete structure (C35/45 material). Verifies the descriptive actors after creating the analysis.

The structure consists of 42 linear elements, 303 planar elements, 202 supports, etc. 370 planar loads are applied: live loads, dead loads and temperature.

2.8 Creating a circle (TTAD #11525)

Test ID: 3607

Test status: Passed

2.8.1 Description Creates a circle.

2.9 Creating a camera (TTAD #11526)

Test ID: 3608

Test status: Passed

2.9.1 Description Verifies the camera creation and visibility.

2.10 Verifying the local axes of a section cut (TTAD #11681)

Test ID: 3637

Test status: Passed

2.10.1 Description Changes the local axes of a section cut in the descriptive model and verifies if the local axes are kept in analysis model.


310

2.11 Verifying the snap points behavior during modeling (TTAD #11458)

Test ID: 3644

Test status: Passed

2.11.1 Description Verifies the snap points behavior when the "Allowed deformation" function is enabled (stretch points) and when it is disabled (grip points).

2.12 Verifying the representation of elements with HEA cross section (TTAD #11328)

Test ID: 3701

Test status: Passed

2.12.1 Description Verifies the representation of elements with HEA340 cross section.

2.13 Verifying the display of the descriptive model in analysis view (TTAD #11462)

Test ID: 3721

Test status: Passed

2.13.1 Description Performs the finite elements calculation and verifies the display of the descriptive model in analysis view.

The structure consists of linear and planar elements.

2.14 Verifying the descriptive model display after post processing results in analysis mode (TTAD #11475)

Test ID: 3733

Test status: Passed

2.14.1 Description Performs the finite elements calculation and displays the forces results on linear elements. Returns to the model mode to verify the descriptive model display.

2.15 Verifying holes in horizontal planar elements after changing the level height (TTAD #11490)

Test ID: 3740

Test status: Passed

2.15.1 Description Verifies holes in horizontal planar elements after changing the level height.


311

2.16 Verifying the display of elements with compound cross sections (TTAD #11486)

Test ID: 3742

Test status: Passed

2.16.1 Description Creates an element with compound cross section (CS1 IPE400 IPE240) and verifies the cross section display.

2.17 Modeling using the tracking snap mode (TTAD #10979)

Test ID: 3745

Test status: Passed

2.17.1 Description Enables the "tracking" snap mode to model structure elements.

2.18 Moving a linear element along with the support (TTAD #12110)

Test ID: 4302

Test status: Passed

2.18.1 Description Moves a linear element along with the element support, after selecting both elements.

2.19 Turning on/off the "ghost" rendering mode (TTAD #11999)

Test ID: 4304

Test status: Passed

2.19.1 Description Verifies the on/off function for the "ghost" rendering mode when the workplane display is disabled.

2.20 Verifying the "ghost display on selection" function for saved views (TTAD #12054)

Test ID: 4347

Test status: Passed

2.20.1 Description Verifies the display of saved views which contain elements with the "ghost on selection" function enabled.


312

2.21 Verifying the "ghost" display after changing the display colors (TTAD #12064)

Test ID: 4349

Test status: Passed

2.21.1 Description Verifies the "ghost" display on selected elements after changing the element display color.

2.22 Verifying the fixed load scale function (TTAD #12183).

Test ID: 4429

Test status: Passed

2.22.1 Description Verifies the "fixed load scale" function.

2.23 Verifying the steel connections modeling (TTAD #11698)

Test ID: 4440

Test status: Passed

2.23.1 Description Verifies the modeling of steel connections.

2.24 Verifying the dividing of planars elements which contain openings (TTAD #12229)

Test ID: 4483

Test status: Passed

2.24.1 Description Verifies the dividing of planars elements which contain openings.

2.25 Verifying the program behavior when trying to create lintel (TTAD #12062)

Test ID: 4507

Test status: Passed

2.25.1 Description Verifies the program behavior when trying to create lintel on a planar element with an inappropriate opening.


313

2.26 Verifying the display of punctual loads after changing the load case number (TTAD #11958)

Test ID: 4508

Test status: Passed

2.26.1 Description Creates a punctual load and verifies the display of the load after placing it in another load case using the load case number from the properties window.

2.27 Verifying the program behavior when launching the analysis on a model with overlapped loads (TTAD #11837)

Test ID: 4511

Test status: Passed

2.27.1 Description Verifies the program behavior when launching the analysis on a model that had overlapped loads.

2.28 Verifying the display of a beam with haunches (TTAD #12299)

Test ID: 4513

Test status: Passed

2.28.1 Description Verifies the display of a beam with haunches, in the "Linear contour" rendering mode.

2.29 Creating base plate connections for non-vertical columns (TTAD #12170)

Test ID: 4534

Test status: Passed

2.29.1 Description Creates a base plate connection on a non-vertical column.

2.30 Verifying drawing of joints in y-z plan (TTAD #12453)

Test ID: 4551

Test status: Passed

2.30.1 Description Verifying drawing of joints in y-z plan (TTAD #12453)


314

2.31 Verifying rotation for steel beam with joint (TTAD #12592)

Test ID: 4560

Test status: Passed

2.31.1 Description Verifying rotation for steel beam with joint at one end (TTAD #12592)

2.32 Verifying annotation on selection (TTAD #12700)

Test ID: 4575

Test status: Passed

2.32.1 Description Verifying annotation on selection (TTAD #12700)

3 Climatic Generator


316

3.1 EC1 NF: generating wind loads on a 3D portal frame with 2 slopes roof (TTAD #11932)

Test ID: 3004

Test status: Passed

3.1.1 Description Generates the wind loads on a concrete structure according to the French Eurocodes 1 standard.

The structure has a roof with two slopes, concrete columns and beams (R20*30 cross section and C20/25 material). The columns have rigid supports.

3.2 EC1: wind load generation on a simple 3D structure with horizontal roof

Test ID: 3099

Test status: Passed

3.2.1 Description Generates wind loads on the windwalls of a concrete structure, according to the Eurocodes 1 standard.

The structure has concrete columns and beams (R20*30 cross section and C20/25 material) and horizontal roof.

3.3 EC1: wind load generation on a high building with horizontal roof

Test ID: 3101

Test status: Passed

3.3.1 Description Generates wind loads on the windwalls of a concrete structure, according to the Eurocodes 1 standard.

The structure is 63m high, has 4 columns and 4 beams (R20*30 cross section and C20/25 material), rigid supports and horizontal roof.

3.4 EC1: wind load generation on a simple 3D portal frame with 2 slopes roof (TTAD #11602)

Test ID: 3103

Test status: Passed

3.4.1 Description Generates wind loads on the windwalls of a concrete structure with 2 slopes roof, according to the Eurocodes 1 standard.

The structure has concrete columns and beams (R20*30 cross section and C20/25 material) and rigid supports.


317

3.5 EC1: wind load generation on simple 3D portal frame with 4 slopes roof (TTAD #11604)

Test ID: 3104

Test status: Passed

3.5.1 Description Generates wind loads on the windwalls of a concrete structure with 4 slopes roof, according to the Eurocodes 1 standard.

The structure has 6 concrete columns (R20*30 cross section and C20/25 material) with rigid supports and C20/25 concrete walls.

3.6 EC1: wind load generation on building with multispan roofs

Test ID: 3106

Test status: Passed

3.6.1 Description Generates wind loads on the windwalls of a concrete structure with multispan roofs, according to the Eurocodes 1 standard.

The structure has concrete columns and beams (R20*30 cross section and C20/25 material) and rigid supports.

3.7 EC1: wind load generation on a signboard

Test ID: 3107

Test status: Passed

3.7.1 Description Generates wind loads on the windwall of a concrete signboard, according to the Eurocodes 1 standard.

The signboard has concrete elements (R20*30 cross section and C20/25 material) and rigid supports.

3.8 EC1: generating wind loads on an isolated roof with 2 slopes (TTAD #11695)

Test ID: 3529

Test status: Passed

3.8.1 Description Generates wind loads on a concrete structure, according to the Eurocodes 1 French standard.

The structure has concrete columns and beams (R20*30 cross section and C20/25 material) and an isolated roof with 2 slopes.


318

3.9 EC1: generating wind loads on duopitch multispan roofs with pitch < 5 degrees (TTAD #11852)

Test ID: 3530

Test status: Passed

3.9.1 Description Generates wind loads on the windwalls of a steel structure, according to the Eurocodes 1 French standard.

The structure has steel columns and beams (I cross section and S275 material), rigid hinge supports and multispan roofs with pitch < 5 degrees.

3.10 EC1: generating wind loads on double slope 3D portal frame with a fully opened face (DEV2012 #1.6)

Test ID: 3535

Test status: Passed

3.10.1 Description Generates wind loads on the windwalls of a concrete structure, according to the Eurocodes 1 French standard.

The structure has concrete columns and beams (R20*30 cross section and C20/25 material), a double slope roof and a fully opened face.

3.11 EC1: generating snow loads on a 2 slopes 3D portal frame with gutter (TTAD #11113)

Test ID: 3603

Test status: Passed

3.11.1 Description Generates snow loads on the windwalls of a 2 slopes 3D portal frame with gutter, according to Eurocodes 1. The structure consists of concrete (C20/25) beams and columns with rigid fixed supports.

3.12 EC1: generating snow loads on a 3D portal frame with horizontal roof and gutter (TTAD #11113)

Test ID: 3604

Test status: Passed

3.12.1 Description Generates snow loads on the windwalls of a 3D portal frame with horizontal roof and gutter, according to Eurocodes 1.

The structure has concrete beams and columns (R20*30 cross section and C20/25 material) with fixed rigid supports.


319

3.13 EC1: snow on a 3D portal frame with horizontal roof and parapet with height reduction (TTAD #11191)

Test ID: 3605

Test status: Passed

3.13.1 Description Generates snow loads on the windwalls of a 3D portal frame with horizontal roof and 2 parapets, according to Eurocodes 1. The height of one parapet is reduced.


3.14 EC1: generating snow loads on a 3D portal frame with a roof which has a small span (< 5m) and a parapet (TTAD #11735)

Test ID: 3606

Test status: Passed

3.14.1 Description Generates snow loads on the windwalls of a 3D portal frame with a roof which has a small span (< 5m) and a parapet, according to Eurocodes 1.


3.15 EC1: generating snow loads on duopitch multispan roofs according to German standards (DIN EN 1991-1-3/NA) (DEV2012 #3.13)

Test ID: 3613

Test status: Passed

3.15.1 Description Generates snow loads on the windwalls of duopitch multispan roofs structure, according to Eurocodes 1 German standards.


3.16 EC1: generating snow loads on monopitch multispan roofs according to German standards (DIN EN 1991-1-3/NA) (DEV2012 #3.13)

Test ID: 3614

Test status: Passed

3.16.1 Description Generates snow loads on the windwalls of monopitch multispan roofs structure, according to Eurocodes 1 German standards.



320

3.17 EC1: generating snow loads on two close roofs with different heights according to German standards (DIN EN 1991-1-3/NA) (DEV2012 #3.13)

Test ID: 3615

Test status: Passed

3.17.1 Description Generates snow loads on two close roofs with different heights, according to Eurocodes 1 German standards.


3.18 EC1: generating wind loads on a 55m high structure according to German standards (DIN EN 1991-1-4/NA) (DEV2012 #3.12)

Test ID: 3618

Test status: Passed

3.18.1 Description Generates wind loads on the windwalls of a 55m high structure, according to Eurocodes 1 German standards.


3.19 EC1: generating wind loads on double slope 3D portal frame according to Czech standards (CSN EN 1991-1-4) (DEV2012 #3.18)

Test ID: 3621

Test status: Passed

3.19.1 Description Generates wind loads on the windwalls of a double slope 3D portal frame, according to the Eurocodes 1 Czech standard (CSN EN 1991-1-4).

The structure has concrete columns and beams (R20*30 cross section and C20/25 material).

3.20 EC1: generating snow loads on two close roofs with different heights according to Czech standards (CSN EN 1991-1-3) (DEV2012 #3.18)

Test ID: 3623

Test status: Passed

3.20.1 Description Generates snow loads on two close roofs with different heights, according to Eurocodes 1 Czech standards.



321

3.21 EC1: generating wind loads on a 2 slopes 3D portal frame with 2 fully opened windwalls (TTAD #11937)

Test ID: 3705

Test status: Passed

3.21.1 Description Generates wind loads on a 2 slopes 3D portal frame with 2 fully opened windwalls, according to the Eurocodes 1 French standards.

The structure has concrete beams and columns (R20*30 cross section and C20/25 material) with rigid fixed supports.

3.22 EC1: generating snow loads on a 2 slopes 3D portal frame with roof thickness greater than the parapet height (TTAD #11943)

Test ID: 3706

Test status: Passed

3.22.1 Description Generates snow loads on a 2 slopes 3D portal frame with roof thickness greater than the parapet height, according to Eurocodes 1 French standard.


3.23 EC1: verifying the snow loads generated on a monopitch frame (TTAD #11302)

Test ID: 3713

Test status: Passed

3.23.1 Description Generates wind loads on the windwalls of a monopitch frame, according to the Eurocodes 1 French standard.

The structure has concrete beams and columns (R20*30 cross section and B20 material) with rigid fixed supports.

3.24 EC1: generating wind loads on a 2 slopes 3D portal frame using the Romanian national annex (TTAD #11687)

Test ID: 4055

Test status: Passed

3.24.1 Description Generates wind loads on the windwalls of a 2 slopes 3D portal frame, according to Eurocodes 1 Romanian standards.

The structure consists of concrete (C20/25) beams and columns with rigid fixed supports.


322

3.25 EC1: generating wind loads on a 2 slopes 3D portal frame (TTAD #11699)

Test ID: 4085

Test status: Passed

3.25.1 Description Generates wind loads on a 2 slopes 3D portal frame according to Eurocodes 1 French standards, using the "Case 1" formula for calculating the turbulence factor.

The structure consits of steel elements with hinge rigid supports.

3.26 EC1: generating snow loads on a 2 slopes 3D portal frame using the Romanian national annex (TTAD #11570)

Test ID: 4086

Test status: Passed

3.26.1 Description Generates snow loads on the windwalls of a 2 slopes 3D portal frame, according to Eurocodes 1 Romanian standards.

The structure consists of concrete (C20/25) beams and columns with rigid fixed supports, with rectangular cross section (R20*30).

3.27 EC1: generating snow loads on a 2 slopes 3D portal frame using the Romanian national annex (TTAD #11569)

Test ID: 4087

Test status: Passed

3.27.1 Description Generates snow loads on the windwalls of a 2 slopes 3D portal frame, according to Eurocodes 1 Romanian standards.


3.28 EC1: generating wind loads on a 2 slopes 3D portal frame (TTAD #11531)

Test ID: 4090

Test status: Passed

3.28.1 Description Generates wind loads on the windwalls of a 2 slopes 3D portal frame, according to Eurocodes 1 French standards - Martinique wind speed.



323

3.29 NV2009: generating wind loads and snow loads on a simple structure with planar support (TTAD #11380)

Test ID: 4091

Test status: Passed

3.29.1 Description Generates wind loads and snow loads on the windwalls of a concrete structure with a planar support, according to NV2009 French standards.

The structure has concrete columns and beams (R20*30 cross section and C20/25 material).

3.30 Generating the description of climatic loads report according to EC1 Romanian standards (TTAD #11688)

Test ID: 4104

Test status: Passed

3.30.1 Description Generates the "Description of climatic loads" report according to EC1 Romanian standards.

The model consists of a steel portal frame with rigid fixed supports. Haunches are defined at both ends of the beams. Dead loads and SR EN 1991-1-4/NB wind loads were generated.

3.31 EC1: Verifying the geometry of wind loads on an irregular shed. (TTAD #12233)

Test ID: 4478

Test status: Passed

3.31.1 Description Verifies the geometry of wind loads on an irregular shed. The wind loads are generated according to Eurocodes 1 - French standard.

3.32 EC1: Verifying the wind loads generated on a building with protruding roof (TTAD #12071, #12278)

Test ID: 4510

Test status: Passed

3.32.1 Description Generates wind loads on the windwalls of a concrete structure with protruding roof, according to the Eurocodes 1 - French standard. Verifies the wind loads from both directions and generates the "Description of climatic loads" report.

The structure has concrete columns and beams (R2*3 cross section and B20 material) and rigid supports.


324

3.33 EC1: generating snow loads on a 2 slopes 3D portal frame (NF EN 1991-1-3/NA) (VT : 3.4 - Snow - Example A)

Test ID: 4518

Test status: Passed

3.33.1 Description Generates snow loads on a 2 slopes 3D portal frame, according to the Eurocodes 1 - French standard (NF EN 1991-1-3/NA)

3.34 EC1: generating wind loads on a 2 slopes 3D portal frame (NF EN 1991-1-4/NA) (VT : 3.1 - Wind - Example A)

Test ID: 4520

Test status: Passed

3.34.1 Description Generates wind loads on a 2 slopes 3D portal frame, according to the Eurocodes 1 - French standard (NF EN 1991-1-4/NA).

3.35 EC1: generating wind loads on a 3D portal frame with one slope roof (NF EN 1991-1-4/NA) (VT : 3.2 - Wind - Example B)

Test ID: 4521

Test status: Passed

3.35.1 Description Generates wind loads on a 3D portal frame with one slope roof, according to the Eurocodes 1 - French standard (NF EN 1991-1-4/NA).

3.36 EC1: generating wind loads on a 2 slopes 3D portal frame (NF EN 1991-1-4/NA) (VT : 3.3 - Wind - Example C)

Test ID: 4523

Test status: Passed

3.36.1 Description Generates wind loads on a 2 slopes 3D portal frame, according to the Eurocodes 1 - French standard (NF EN 1991-1-4/NA).


325

3.37 EC1: generating wind loads on a triangular based lattice structure with composed profiles and automatic calculation of "n" (NF EN 1991-1-4/NA) (TTAD #12276).

Test ID: 4525

Test status: Passed

3.37.1 Description Generates the wind loads on a triangular based lattice structure with composed profiles, using automatic calculation of "n" - eigen mode frequency (NF EN 1991-1-4/NA). The wind loads are generated according to Eurocodes 1 - French standards.

3.38 EC1: wind loads on a triangular based lattice structure with composed profiles and user imposed n (NF EN 1991-1-4/NA) (TTAD #12276).

Test ID: 4526

Test status: Passed

3.38.1 Description EC1: wind loads on a triangular based lattice structure with composed profiles using user imposed n - eigen mode frequency - (NF EN 1991-1-4/NA) (TTAD #12276).

3.39 EC1: generating snow loads on a 3 slopes 3D portal frame with parapets (NF EN 1991-1-3/NA) (TTAD #11111)

Test ID: 4546

Test status: Passed

3.39.1 Description Generates snow loads on a 3 slopes 3D portal frame with parapets, according to the Eurocodes 1 - French standard (NF EN 1991-1-3/NA)

3.40 EC1: Generating snow loads on a 4 slopes shed with gutters. (TTAD #12528)

Test ID: 4568

Test status: Passed

3.40.1 Description EC1: Generates snow loads on a 4 slopes shed with gutters on each slope and lateral parapets, according to the Eurocodes 1 - French standard (NF EN 1991-1-3/NA).


326

3.41 EC1: Generating snow loads on a 4 slopes shed with gutters. (TTAD #12528)

Test ID: 4569

Test status: Passed

3.41.1 Description EC1: Generates snow loads on a 4 slopes shed with gutters on each slope and middle parapets, according to the Eurocodes 1 - French standard (NF EN 1991-1-3/NA).

3.42 EC1: Generating snow loads on a single slope with lateral parapets. (TTAD #12606)

Test ID: 4570

Test status: Passed

3.42.1 Description EC1: Generates snow loads on a single slope with lateral parapets, according to the Eurocodes 1 - French standard (NF EN 1991-1-3/NA).

3.43 EC1: generating wind loads on a sqaure based lattice structure with composed profiles and automatic calculation of "n" (NF EN 1991-1-4/NA) (TTAD #12744).

Test ID: 4580

Test status: Passed

3.43.1 Description Generates the wind loads on a square based lattice structure with composed profiles, using automatic calculation of "n" - eigen mode frequency. The wind loads are generated according to Eurocodes 1 - French standards (NF EN 1991-1-4/NA).

3.44 NV2009: Verifying wind and snow reports for a protruding roof (TTAD #11318)

Test ID: 4536

Test status: Passed

3.44.1 Description Generates wind loads and snow loads according to NV2009 - French climatic standards. Verifies wind and snow reports for a protruding roof.

3.45 NV2009: Generating wind loads on a 2 slopes 3D portal frame at 15 height. (TTAD #12604)

Test ID: 4567

Test status: Passed

3.45.1 Description Generates wind loads on a 2 slopes 3D portal frame at 15 height, according to the French standard (NV2009).

4 Combinations


328

4.1 Generating combinations (TTAD #11673)

Test ID: 3471

Test status: Passed

4.1.1 Description Generates concomitance between three types of loads applied on a structure (live loads, dead loads and seismic loads - EN 1998-1), using the quadratic combination function. Generates the combinations description report and the point support actions by element report.

4.2 Generating combinations for NEWEC8.cbn (TTAD #11431)

Test ID: 3746

Test status: Passed

4.2.1 Description Generates combinations for NEWEC8.cbn.

4.3 Defining concomitance rules for 2 case families (TTAD #11355)

Test ID: 3749

Test status: Passed

4.3.1 Description Generates live loads and dead loads on a steel structure. Defines the concomitance rules between the two load case families and generates the concomitance matrix.

4.4 Generating load combinations with unfavorable and favorable/unfavorable predominant action (TTAD #11357)

Test ID: 3751

Test status: Passed

4.4.1 Description Generates load combinations with unfavorable and favorable/unfavorable predominant action. Predominant action is a case family with 2 static load cases.

4.5 Generating load combinations after changing the load case number (TTAD #11359)

Test ID: 3756

Test status: Passed

4.5.1 Description Generates load combinations with concomitance matrix after changing the load case number. A report with the combinations description is generated.


329

4.6 Generating concomitance matrix after adding a new dead load case (TTAD #11361)

Test ID: 3766

Test status: Passed

4.6.1 Description Creating a new dead load case, after 2 case families were created, and generate concomitance matrix. A report with combinations description is generated.

4.7 Generating the concomitance matrix after switching back the effect for live load (TTAD #11806)

Test ID: 4219

Test status: Passed

4.7.1 Description Generates the concomitance matrix and the combinations description reports after switching back the effect for live load.

4.8 Generating a set of combinations with seismic group of loads (TTAD #11889)

Test ID: 4350

Test status: Passed

4.8.1 Description Generates a set of combinations with seismic group of loads.

4.9 Generating a set of combinations with Q group of loads (TTAD #11960)

Test ID: 4353

Test status: Passed

4.9.1 Description Generates a set of combinations with Q group of loads.


330

4.10 Generating a set of combinations with different Q "Base" types (TTAD #11806)

Test ID: 4357

Test status: Passed

4.10.1 Description Generates a set of combinations with different Q "Base" types

1 - G

2 - Q - Base

3 - G

4 - Q -Base or acco

Generates the first set of combinations and the first combinations report.

1 - G

2 - Q - Base

3 - G

4 - Q -Base

Generates the second set of combinations and the second combinations report.


331

4.11 Performing the combinations concomitance standard test no.1 (DEV2010#1.7)

Test ID: 4382

Test status: Passed

4.11.1 Description Generates loads:

1 - G (Favorable or Unfavorable)

2 - Q (Base or Acco)

3 - Q (Acco)

Generates combinations. Generates the combinations report.

4.12 Performing the combinations concomitance standard test no.2 (DEV2012 #1.7)

Test ID: 4384

Test status: Passed





3 - Q (Base)



332


Test ID: 4386

Test status: Passed








Test ID: 4391

Test status: Passed



2 - Q (Base)


4 - Q (Base)



333


Test ID: 4394

Test status: Passed




3 - E (Base) - only one seimic load !


Set value "0" (exclusive) between seismic and all Q loads (seism only combination).



Test ID: 4397

Test status: Passed




3 - E (Base) - only one seismic load



334


Test ID: 4405

Test status: Passed

4.17.1 Description Creates loads:




4 - Q (Acco)

5 - Acc (Base)



Test ID: 4407

Test status: Passed



2 - Q Group(Base or Acco)

2 - Q

3 - Q

4 - Q


6 - Snow (Base or Acco)


Un-group 2-Q Group to independent 2-Q, 3-Q, 4-Q loads.



335


Test ID: 4408

Test status: Passed




3 - E Group (Base)

3 - EX

4 - EY

5 - EZ

Un-group 3 - E Group to independent loads : 3 - EX 4 - EY 5 - EZ



Test ID: 4409

Test status: Passed




3 - E Group(Base)

3 - EX

4 - EY

5 - EZ

Defines the seismic group type as "Quadratic".


Resets the combination set. Defines the seismic group type as "Newmark".



336

4.21 Verifying combinations for CZ localization (TTAD #12542)

Test ID: 4550

Test status: Passed

4.21.1 Description Verifies simplified combinations for CZ localization.

4.22 Verifying the combinations description report (TTAD #11632)

Test ID: 3544

Test status: Passed

4.22.1 Description Generates a dead load case, two live load cases and a snow load case, defines the concomitance between the generated load cases and generates the combinations description report.

5 Concrete Design


338

5.1 EC2: column design with “Nominal Stiffnes method” square section (TTAD #11625)

Test ID: 3001

Test status: Passed

5.1.1 Description Verifies and generates the corresponding report for the longitudinal reinforcement bars of a column. The column is designed with "Nominal stiffness method", with a square cross section (C40).

5.2 Verifying reinforced concrete results on a structure with 375 load cases combinations (TTAD #11683)

Test ID: 3475

Test status: Passed

5.2.1 Description Verifies the reinforced concrete results for a model with more than 100 load cases combinations.

On a concrete structure there are applied: dead loads, self weight, live loads, wind loads (according to NV2009) and accidental loads. A number of 375 combinations are obtained. Performs the finite elements calculation and the reinforced concrete calculation. Generates the reinforcement areas planar elements report.

5.3 EC2 : calculation of a square column in traction (TTAD #11892)

Test ID: 3509

Test status: Passed

5.3.1 Description The test is performed on a single column in tension, according to Eurocodes 2.

The column has a section of 20 cm square and a rigid support. A permanent load (traction of 100 kN) and a live load (40 kN) are applied.

Performs the finite elements calculation and the reinforced concrete calculation. Generates the longitudinal reinforcement report.

5.4 Verifying Aty and Atz for a fixed concrete beam (TTAD #11812)

Test ID: 3528

Test status: Passed

5.4.1 Description Performs the finite elements calculation and the reinforced concrete calculation of a model with a horizontal concrete beam.

The beam has a R20*50 cross section and two hinge rigid supports.

Verifies Aty and Atz for the fixed concrete beam.


339

5.5 Verifying the reinforced concrete results on a fixed beam (TTAD #11836)

Test ID: 3542

Test status: Passed

5.5.1 Description Verifies the concrete results on a fixed horizontal beam.

Performs the finite elements calculation and the reinforced concrete calculation. Generates the reinforced concrete calculation results report.

The beam has a R25*60 cross section, C25/30 material and has a rigid hinge support at one end and a rigid suport with translation restraints on Y and Z at the other end. A linear dead load (-28.75 kN) and a live load (-50.00 kN) are applied.

5.6 Verifying the longitudinal reinforcement bars for a filled circular column (TTAD #11678)

Test ID: 3543

Test status: Passed

5.6.1 Description Verifies the longitudinal reinforcement for a vertical concrete bar.

Performs the finite elements calculation and the reinforced concrete calculation. Generates the reinforcement report.

The bar has a circular cross section with a radius of 40.00 cm, has a rigid hinge support and a vertical punctual load of -5000.00 kN is applied.

5.7 Verifying longitudinal reinforcement for linear element (TTAD #11636)

Test ID: 3545

Test status: Passed

5.7.1 Description Verifies the longitudinal reinforcement for a vertical concrete bar.

Performs the finite elements calculation and the reinforced concrete calculation. Verifies the longitudinal reinforcement and generates the reinforcement report.

The bar has a square cross section of 30.00 cm, has a rigid fixed support at the base and a support with translation restraints on X and Y. A vertical punctual load of -1260.00 kN is applied.


340

5.8 Verifying the longitudinal reinforcement for a fixed linear element (TTAD #11700)

Test ID: 3547

Test status: Passed

5.8.1 Description Verifies the longitudinal reinforcement for a horizontal concrete bar.

Performs the finite elements calculation and the reinforced concrete calculation. Verifies the longitudinal reinforcement and generates the reinforcement report.

The bar has a rectangular cross section R40*80, has a rigid hinge support at one end and a rigid support with translation restraints on Y and Z. Four loads are applied: a linear dead load of -50.00 kN on FZ, a punctual dead load of -30.00 kN on FZ, a linear live load of -60.00 kN on FZ and a punctual live load of -25.00 kN on FZ.

5.9 Verifying concrete results for planar elements (TTAD #11583)

Test ID: 3548

Test status: Passed

5.9.1 Description Verifies the reinforcement results on planar elements.

Performs the finite elements calculation and the reinforced concrete calculation. Generates the reinforced concrete analysis report: data and results.

The model consists of two planar elements (C20/25 material) with rigid fixed linear supports. On each element, a punctual load of 50.00 kN on FX is applied.

5.10 Verifying concrete results for linear element (TTAD #11556)

Test ID: 3549

Test status: Passed

5.10.1 Description Verifies the reinforcement results for a horizontal concrete bar.

Performs the finite elements calculation and the reinforced concrete calculation. Verifies the reinforcement and generates the reinforced concrete analysis report: data and results.

The bar has a rectangular cross section R20*50, has a rigid hinge support at one end and a rigid support with translation restraints on X, Y and Z and rotation restraint on X.

5.11 Verifying reinforcement for concrete column (TTAD #11635)

Test ID: 3564

Test status: Passed

5.11.1 Description Verifying reinforcement for concrete column (TTAD:#11635)


341

5.12 Verifying the minimum transverse reinforcement area results for an articulated beam (TTAD #11342)

Test ID: 3638

Test status: Passed

5.12.1 Description Verifies the minimum transverse reinforcement area for an articulated horizontal beam.

Performs the finite elements calculation and the reinforced concrete calculation and generates the "Transverse reinforcement linear elements" report.

The beam has a rectangular cross section (R20*50), B25 material and two hinge rigid supports at both ends.

5.13 Verifying the minimum transverse reinforcement area results for articulated beams (TTAD #11342)

Test ID: 3639

Test status: Passed

5.13.1 Description Verifies the minimum transverse reinforcement area for two articulated horizontal beams.

Performs the finite elements calculation and the reinforced concrete calculation and generates the "Transverse reinforcement linear elements" report.

Each beam has rectangular cross section (R30*70), B25 material and two hinge rigid supports at both ends. On each beam there are applied dead loads: a linear load of -25.00 kN and two punctual loads of -55.00 kN and -65.00 kN; and live loads: a linear load of -20.00 kN and two punctual loads of -40.00 kN and -35.00 kN.

5.14 Verifying the longitudinal reinforcement for a horizontal concrete bar with rectangular cross section

Test ID: 4179

Test status: Passed

5.14.1 Description Performs the finite elements calculation and the reinforced concrete calculation according to the Eurocodes 2 - French DAN. Verifies the longitudinal reinforcement and generates the corresponding report: "Longitudinal reinforcement linear elements".

The model consists of a concrete linear element with rectangular cross section (R18*60) with rigid hinge supports at both ends and two linear vertical loads: -15.40 kN and -9.00 kN.


342

5.15 EC2: Verifying the minimum reinforcement area for a simply supported beam

Test ID: 4517

Test status: Passed

5.15.1 Description Verifies the minimum reinforcement area for a concrete simply supported beam subjected to self weight. The verification is made with Eurocodes 2 - French annex.

5.16 EC2: Verifying the longitudinal reinforcement area of a beam under a linear load

Test ID: 4519

Test status: Passed

5.16.1 Description Verifies the longitudinal reinforcement area of a beam under a linear load (horizontal level behavior law).

Verification is done with Eurocodes 2 norm French Annex.

5.17 EC2: Verifying the longitudinal reinforcement area of a beam under a linear load - inclined stress strain behavior law

Test ID: 4522

Test status: Passed

5.17.1 Description Verifies the longitudinal reinforcement area of a beam under a linear load - inclined stress strain behavior law.

Verification is done according to Eurocodes 2 norm with French Annex.

5.18 EC2: Verifying the longitudinal reinforcement area for a beam subjected to point loads

Test ID: 4527

Test status: Passed

5.18.1 Description Verifies the longitudinal reinforcement area for a beam subjected to point loads (applied at the middle of the beam).

Verification is done according EC2 norm with French Annex.


343

5.19 EC2: Verifying the longitudinal reinforcement area of a beam uner a linear load - bilinear stress-strain diagram

Test ID: 4541

Test status: Passed

5.19.1 Description Verifies the longitudinal reinforcement area of a simply supported beam under a linear load - bilinear stress-strain diagram.

Verification is done according to Eurocodes 2 norm with French Annex.

5.20 Modifying the "Design experts" properties for concrete linear elements (TTAD #12498)

Test ID: 4542

Test status: Passed

5.20.1 Description Defines the "Design experts" properties for a concrete (EC2) linear element in analysis model and verifies properties from descriptive model.

5.21 EC2: Verifying the transverse reinforcement area for a beam subjected to linear loads

Test ID: 4555

Test status: Passed

5.21.1 Description Verifies the transverse reinforcement area for a beam subjected to linear loads. The verification is made according EC2 norm with French Annex.

5.22 EC2: Verifying the longitudinal reinforcement are of a beam under a linear load - horizontal level behavior law

Test ID: 4557

Test status: Passed

5.22.1 Description Verifies the longitudinal reinforcement area of a beam under self-weight and linear loads - horizontal level behavior law. The verification is made according EC2 norm with French Annex.

6 General Application


346

6.1 Verifying geometry properties of elements with compound cross sections (TTAD #11601)

Test ID: 3546

Test status: Passed

6.1.1 Description Verifies the geometry properties of a steel structure with elements which have compound cross sections (CS4 IPE330 UPN240). Generates the geometrical data report.

6.2 Verifying material properties for C25/30 (TTAD #11617)

Test ID: 3571

Test status: Passed

6.2.1 Description Verifies the material properties on a model with a concrete (C25/30) bar. Generates the material description report.

6.3 Verifying the synthetic table by type of connection (TTAD #11422)

Test ID: 3646

Test status: Passed

6.3.1 Description Performs the finite elements calculation and the steel calculation on a structure with four types of connections. Generates the "Synthetic table by type of connection" report.

The structure consists of linear steel elements (S275) with CE505, IPE450, IPE140 and IPE500 cross section. The model connections: columns base plates, beam - column fixed connections, beam - beam fixed connections and gusset plate. Live loads, snow loads and wind loads are applied.

6.4 Importing a cross section from the Advance Steel profiles library (TTAD #11487)

Test ID: 3719

Test status: Passed

6.4.1 Description Imports the Canam Z 203x10.0 section from the Advance Steel Profiles library in the Advance Design list of available cross sections.


347

6.5 Creating and updating model views and post-processing views (TTAD #11552)

Test ID: 3820

Test status: Passed

6.5.1 Description Creates and updates the model view and the post-processing views for a simple steel frame.

6.6 Verifying mesh, CAD and climatic forces - LPM meeting

Test ID: 4079

Test status: Passed

6.6.1 Description Generates the "Description of climatic loads" report for a model consisting of a concrete structure with dead loads, wind loads, snow loads and seism loads. Performs the model verification, meshing and finite elements calculation. Generates the "Displacements of linear elements by element" report.

6.7 Creating a new Advance Design file using the "New" command from the "Standard" toolbar (TTAD #12102)

Test ID: 4095

Test status: Passed

6.7.1 Description Creates a new .fto file using the "New" command from the "Standard" toolbar. Creates a rigid punctual support and tests the CAD coordinates.

6.8 Launching the verification of a model containing steel connections (TTAD #12100)

Test ID: 4096

Test status: Passed

6.8.1 Description Launches the verification function for a model containing a beam-column steel connection.


348

6.9 Verifying the appearance of the local x orientation legend (TTAD #11737)

Test ID: 4109

Test status: Passed

6.9.1 Description Verifies the color legend display. On a model with a planar element, the color legend is enabled; it displays the elements by the local x orientation color.

6.10 Creating system trees using the copy/paste commands (DEV2012 #1.5)

Test ID: 4162

Test status: Passed

6.10.1 Description Creates system trees using the copy/paste commands in the Pilot. The source system consists of several subsystems. The target system is on the same level as the source system.

6.11 Creating system trees using the copy/paste commands (DEV2012 #1.5)

Test ID: 4164

Test status: Passed

6.11.1 Description Creates system trees using the copy/paste commands in the Pilot. The source system consists of several subsystems. The target system is in the source system.

6.12 Verifying the objects rename function (TTAD #12162)

Test ID: 4229

Test status: Passed

6.12.1 Description Verifies the renaming function from the properties list of a linear element. The name contains the "_" character.


349

6.13 Generating liquid pressure on horizontal and vertical surfaces (TTAD #10724)

Test ID: 4361

Test status: Passed

6.13.1 Description Generates liquid pressure on a concrete structure with horizontal and vertical surfaces. Generates the loadings description report.

6.14 Changing the default material (TTAD #11870)

Test ID: 4436

Test status: Passed

6.14.1 Description Selects a different default material for concrete elements.

6.15 Verifying 2 joined vertical elements with the clipping option enabled (TTAD #12238)

Test ID: 4480

Test status: Passed

6.15.1 Description Performs the finite elements calculation on a model with 2 joined vertical elements with the clipping option enabled.

6.16 Defining the reinforced concrete design assumptions (TTAD #12354)

Test ID: 4528

Test status: Passed

6.16.1 Description Verifies the definition of the reinforced concrete design assumptions.


350

6.17 Verifying precision for linear and planar concrete cover (TTAD #12525)

Test ID: 4547

Test status: Passed

6.17.1 Description Verifies the linear and planar concrete cover precision.

6.18 Verifying element creation using commas for coordinates (TTAD #11141)

Test ID: 4554

Test status: Passed

6.18.1 Description Verifies element creation using commas for coordinates in the command line.

7 Import / Export


352

7.1 Verifying the export of a linear element to GTC (TTAD #10932, TTAD #11952)

Test ID: 3628

Test status: Passed

7.1.1 Description Exports a linear element to GTC.

7.2 Exporting an Advance Design model to DO4 format (DEV2012 #1.10)

Test ID: 4101

Test status: Passed

7.2.1 Description Launches the "Export > Text file" command and saves the current project as a .do4 archive file.

The model contains all types of structural elements, loads and geometric objects.

7.3 Exporting an analysis model to ADA (through GTC) (DEV2012 #1.3)

Test ID: 4193

Test status: Passed

7.3.1 Description Exports the analysis model to ADA (through GTC) with:

- Export results: enabled

- Export meshed model: disabled

7.4 Exporting an analysis model to ADA (through GTC) (DEV2012 #1.3)

Test ID: 4195

Test status: Passed

7.4.1 Description Exports the analysis model to ADA (through GTC) with:

- Export results: disabled

- Export meshed model: enabled

7.5 Importing GTC files containing elements with haunches from SuperSTRESS (TTAD #12172)

Test ID: 4297

Test status: Passed

7.5.1 Description Imports a GTC file from SuperSTRESS. The file contains steel linear elements with haunch sections.


353

7.6 Importing GTC files containing elements with circular hollow sections, from SuperSTRESS (TTAD #12197)

Test ID: 4388

Test status: Passed

7.6.1 Description Imports a GTC file from SuperSTRESS. The file contains elements with circular hollow section. Verifies if the cross sections are imported from the attached "UK Steel Sections" database.

7.7 Importing GTC files containing elements with circular hollow sections, from SuperSTRESS (TTAD #12197)

Test ID: 4389

Test status: Passed

7.7.1 Description Imports a GTC file from SuperSTRESS when the "UK Steel Sections" database is not attached. The file contains elements with circular hollow section. Verifies the cross sections definition.

7.8 Verifying the GTC files exchange between Advance Design and SuperSTRESS (DEV2012 #1.9)

Test ID: 4445

Test status: Passed

7.8.1 Description Verifies the GTC files exchange (import/export) between Advance Design and SuperSTRESS.

7.9 System stability when importing AE files with invalid geometry (TTAD #12232)

Test ID: 4479

Test status: Passed

7.9.1 Description Imports a complex model containing elements with invalid geometry.

7.10 Verifying the releases option of the planar elements edges after the model was exported and imported via GTC format (TTAD #12137)

Test ID: 4506

Test status: Passed

7.10.1 Description Exports to GTC a model with planar elements on which the edges releases were defined. Imports the GTC file to verify the planar elements releases option.


354

7.11 Verifying the load case properties from models imported as GTC files (TTAD #12306)

Test ID: 4515

Test status: Passed

7.11.1 Description Performs the finite elements calculation on a model with dead load cases and exports the model to GTC. Imports the GTC file to verify the load case properties.

7.12 Exporting linear elements to IFC format (TTAD #10561)

Test ID: 4530

Test status: Passed

7.12.1 Description Exports to IFC format a model containing linear elements having sections of type "I symmetric" and "I assymetric".

7.13 Importing IFC files containing continuous foundations (TTAD #12410)

Test ID: 4531

Test status: Passed

7.13.1 Description Imports an IFC file containing a continuous foundation (linear support) and verifies the element display.

7.14 Importing GTC files containing "PH.RDC" system (TTAD #12055)

Test ID: 4548

Test status: Passed

7.14.1 Description Imports a GTC file exported from Advance Design. The file contains the automatically created system "PH.RDC".

7.15 Exporting meshed model to GTC (TTAD #12550)

Test ID: 4552

Test status: Passed

7.15.1 Description Exports meshed model to GTC. The meshed planar element from the model contains a triangular mesh.

8 Connection Design


356

8.1 Creating connections groups (TTAD #11797)

Test ID: 4250

Test status: Passed

8.1.1 Description Verifies the connections groups function.

8.2 Deleting a welded tube connection - 1 gusset bar (TTAD #12630)

Test ID: 4561

Test status: Passed

8.2.1 Description Deletes a welded tube connection - 1 gusset bar after the joint was exported to ADSC.

9 Mesh


358

9.1 Creating triangular mesh for planar elements (TTAD #11727)

Test ID: 3423

Test status: Passed

9.1.1 Description Creates a triangular mesh on a planar element with rigid supports and self weight.

9.2 Verifying mesh points (TTAD #11748)

Test ID: 3458

Test status: Passed

9.2.1 Description Performs the finite elements calculation and verifies the mesh nodes of a concrete structure.

The structure consists of concrete linear elements (R20*20 corss section) and rigid supports; the loads applied on the structure: dead loads, live loads, wind loads and snow loads, according to Eurocodes.

9.3 Verifying the mesh for a model with generalized buckling (TTAD #11519)

Test ID: 3649

Test status: Passed

9.3.1 Description Performs the finite elements calculation and verifies the mesh for a model with generalized buckling.

10 Reports Generator


360

10.1 Generating the critical magnification factors report (TTAD #11379)

Test ID: 3647

Test status: Passed

10.1.1 Description Performs the finite elements calculation and the steel calculation on a structure with four types of connections. Generates the "Synthetic table by type of connection" report.

The structure consists of linear steel elements (S275) with CE505, IPE450, IPE140 and IPE500 cross section. The model connections: columns base plates, beam - column fixed connections, beam - beam fixed connections and gusset plate. Live loads, snow loads and wind loads are applied.

10.2 Modal analysis: eigen modes results for a structure with one level

Test ID: 3668

Test status: Passed

10.2.1 Description Performs the finite elements calculation and generates the "Characteristic values of eigen modes" report.

The one-level structure consists of concrete linear and planar elements with rigid supports. A modal analysis is defined.

10.3 System stability when the column releases interfere with support restraints (TTAD #10557)

Test ID: 3717

Test status: Passed

10.3.1 Description Performs the finite elements calculation and generates the systems description report for a structure which has column releases that interfere with the supports restraints.

The structure consists of steel beams and steel columns (S235 material, HEA550 cross section) with rigid fixed supports.

10.4 Generating a report with modal analysis results (TTAD #10849)

Test ID: 3734

Test status: Passed

10.4.1 Description Generates a report with modal results for a model with seismic action defined.


361

10.5 Creating the rules table (TTAD #11802)

Test ID: 4099

Test status: Passed

10.5.1 Description Generates the "Rules description" report as .rtf and .txt file.

The model consists of a steel structure with supports and a base plate connection. Two rules were defined for the steel calculation.

10.6 Creating the steel materials description report (TTAD #11954)

Test ID: 4100

Test status: Passed

10.6.1 Description Generates the "Steel materials" report as a .txt file.

The model consists of a steel structure with supports and a base plate connection.

10.7 Verifying the model geometry report (TTAD #12201)

Test ID: 4467

Test status: Passed

10.7.1 Description Generates the "Model geometry" report to verify the model properties: total weight, largest structure dimensions, center of gravity.

10.8 Verifying the global envelope of linear elements forces result (on each 1/4 of mesh element) (TTAD #12230)

Test ID: 4486

Test status: Passed

10.8.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements forces results on each 1/4 of mesh element by generating the "Global envelope of linear elements forces result report".

The model consists of a concrete portal frame with rigid fixed supports.


362

10.9 Verifying the global envelope of linear elements forces result (on all quarters of super element) (TTAD #12230)

Test ID: 4487

Test status: Passed

10.9.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements forces results on all quarters of super element by generating the "Global envelope of linear elements forces result report".


10.10 Verifying the global envelope of linear elements forces result (on end points and middle of super element) (TTAD #12230)

Test ID: 4488

Test status: Passed

10.10.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements forces results on end points and middle of super element by generating the "Global envelope of linear elements forces result report".


10.11 Verifying the global envelope of linear elements forces result (on start and end of super element) (TTAD #12230)

Test ID: 4489

Test status: Passed

10.11.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements forces results on the start and end of super element by generating the "Global envelope of linear elements forces result report".


10.12 Verifying signed concomitant linear elements envelopes on Fx report (TTAD #11517)

Test ID: 3576

Test status: Passed

10.12.1 Description Performs the finite elements calculation on a concrete structure. Generates the "Signed concomitant linear elements envelopes on Fx report".

The structure has concrete beams and columns, two concrete walls and a windwall. Loads applied on the structure: self weight and a planar live load of -40.00 kN.


363

10.13 Verifying the global envelope of linear elements forces result (on the start point of super element) (TTAD #12230)

Test ID: 4490

Test status: Passed

10.13.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements forces results on the start point of super element by generating the "Global envelope of linear elements forces result report".


10.14 Verifying the global envelope of linear elements forces result (on the end point of super element) (TTAD #12230, #12261)

Test ID: 4491

Test status: Passed

10.14.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements forces results on the end point of super element by generating the "Global envelope of linear elements forces result report".


10.15 Verifying the global envelope of linear elements displacements (on each 1/4 of mesh element) (TTAD #12230)

Test ID: 4492

Test status: Passed

10.15.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements displacements on each 1/4 of mesh element by generating the "Global envelope of linear elements displacements report".


10.16 Verifying the global envelope of linear elements displacements (on all quarters of super element) (TTAD #12230)

Test ID: 4493

Test status: Passed

10.16.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements displacements on all quarters of super element by generating the "Global envelope of linear elements displacements report".



364

10.17 Verifying the global envelope of linear elements displacements (on end points and middle of super element) (TTAD #12230)

Test ID: 4494

Test status: Passed

10.17.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements displacements on end points and middle of super element by generating the "Global envelope of linear elements displacements report".


10.18 Verifying the global envelope of linear elements displacements (on start and end of super element) (TTAD #12230)

Test ID: 4495

Test status: Passed

10.18.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements displacements on start and end of super element by generating the "Global envelope of linear elements displacements report".


10.19 Verifying the global envelope of linear elements displacements (on the start point of super element) (TTAD #12230)

Test ID: 4496

Test status: Passed

10.19.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements displacements on the start point of super element by generating the "Global envelope of linear elements displacements report".


10.20 Verifying the global envelope of linear elements displacements (on the end point of super element) (TTAD #12230, TTAD #12261)

Test ID: 4497

Test status: Passed

10.20.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements displacements on the end point of super element by generating the "Global envelope of linear elements displacements report".



365

10.21 Verifying the global envelope of linear elements stresses (on each 1/4 of mesh element) (TTAD #12230)

Test ID: 4498

Test status: Passed

10.21.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements stresses on each 1/4 of mesh element by generating the "Global envelope of linear elements stresses report".


10.22 Verifying the global envelope of linear elements stresses (on all quarters of super element) (TTAD #12230)

Test ID: 4499

Test status: Passed

10.22.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements stresses on all quarters of super element by generating the "Global envelope of linear elements stresses report".


10.23 Verifying the global envelope of linear elements stresses (on end points and middle of super element) (TTAD #12230)

Test ID: 4500

Test status: Passed

10.23.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements stresses on end points and middle of super element by generating the "Global envelope of linear elements stresses report".


10.24 Verifying the global envelope of linear elements stresses (on start and end of super element) (TTAD #12230)

Test ID: 4501

Test status: Passed

10.24.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements stresses on start and end of super element by generating the "Global envelope of linear elements stresses report".



366

10.25 Verifying the global envelope of linear elements stresses (on the start point of super element) (TTAD #12230)

Test ID: 4502

Test status: Passed

10.25.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements stresses on the start point of super element by generating the "Global envelope of linear elements stresses report".


10.26 Verifying the global envelope of linear elements stresses (on the end point of super element) (TTAD #12230, TTAD #12261)

Test ID: 4503

Test status: Passed

10.26.1 Description Performs the finite elements calculation and verifies the global envelope of linear elements stresses on the end point of super element by generating the "Global envelope of linear elements stresses report".


10.27 Verifying the Min/Max values from the user reports (TTAD# 12231)

Test ID: 4505

Test status: Passed

10.27.1 Description Performs the finite elements calculation and generates a user report containing the results of Min/Max values.

10.28 Verifying the shape sheet for a steel beam (TTAD #12455)

Test ID: 4535

Test status: Passed

10.28.1 Description Verifies the shape sheet for a steel beam.

10.29 Verifying the EC2 calculation assumptions report (TTAD #11838)

Test ID: 4544

Test status: Passed

10.29.1 Description Verifies the EC2 calculation assumptions report.


367

10.30 Verifying the shape sheet report (TTAD #12353)

Test ID: 4545

Test status: Passed

10.30.1 Description Verifies the shape sheet report.

10.31 Verifying the Max row on the user table report (TTAD #12512)

Test ID: 4558

Test status: Passed

10.31.1 Description Verifies the Max row on the user table report.

10.32 Verifying the shape sheet strigs display (TTAD #12622)

Test ID: 4559

Test status: Passed

10.32.1 Description Verifies the shape sheet strings display for a steel beam with circular hollow cross-section.

10.33 Verifying the steel shape sheet display (TTAD #12657)

Test ID: 4562

Test status: Passed

10.33.1 Description Verifies the steel shape sheet display when the fire calculation is disabled.

10.34 Verifying report for modal analysis (TTAD #12718)

Test ID: 4576

Test status: Passed

10.34.1 Description Generating report for modal analysis (TTAD #12718)

11 Seismic Analysis


370

11.1 EC8 : Verifying the displacements results of a liniar element according to Czech seismic standards (CSN EN 1998-1) (DEV2012 #3.18)

Test ID: 3626

Test status: Passed

11.1.1 Description Verifies the displacements results of an inclined linear element according to Eurocodes 8 Czech standard. Performs the finite elements calculation and generates the displacements of linear elements by load case and by element reports.

The concrete element (C20/25) has R20*30 cross section and a rigid point support. The loads applied on the element: self weight and seismic loads (CSN EN 1998-1).

11.2 Verifying the spectrum results for EC8 seism (TTAD #11478)

Test ID: 3703

Test status: Passed

11.2.1 Description Performs the finite elements calculation and generates the "Displacements of linear elements by load case" report for a concrete beam with rectangular cross section R20*30 with fixed rigid punctual support. Model loads: self weight and seismic loads according to Eurocodes 8 French standards.

11.3 Verifying the spectrum results for EC8 seism (TTAD #12472)

Test ID: 4537

Test status: Passed

11.3.1 Description Performs the finite elements calculation and generates the "Displacements of linear elements by load case" report for a concrete beam with rectangular cross section R20*30 with fixed rigid punctual support. Model loads: self weight and seismic loads according to Eurocodes 8 Romanian standards(SR EN 1998-1/NA).

12 Steel Design


372

12.1 Verifying results on square hollowed beam 275H according to thickness (TTAD #11770)

Test ID: 3406

Test status: Passed

12.1.1 Description Performs the steel calculation for two vertical bars with different thicknesses and generates the shape sheets report.

The bars are made of the same material (S275 H - EN 10210-1), have rectangular hollow cross sections, but with different thicknesses (R80*40/4.1 and R80*40/3.9). Each is subjected to a -150.00 kN vertical live load and has a rigid support.

12.2 Verifying shape sheet on S275 beam (TTAD #11731)

Test ID: 3434

Test status: Passed

12.2.1 Description Performs the steel calculation for two horizontal bars and generates the shape sheets report.

The bars have cross sections from different catalogues (1016x305x487 UKB and UKB1016x305x487). They are made of the same material (S275); each is subjected to a -500.00 kN linear horizontal dead load and has two rigid supports at both ends.

12.3 Verifying the calculation results for steel cables (TTAD #11623)

Test ID: 3560

Test status: Passed

12.3.1 Description Performs the finite elements calculation and the steel calculation for a steel model with cables (D4) and a static nonlinear case. Generates the steel analysis report: data and results.

12.4 Generating the shape sheet by system (TTAD #11471)

Test ID: 3575

Test status: Passed

12.4.1 Description Generates shape sheets by system, on a model with 2 systems.


373

12.5 Verifying the shape sheet results for the elements of a simple vault (TTAD #11522)

Test ID: 3612

Test status: Passed

12.5.1 Description Performs the finite elements calculation and the steel calculation. Generates the shape sheet results report.

The structure is a simple vault consisting of three steel elements (S235 material, IPEA240 cross section) with two rigid fixed supports. The loads applied on the structure: self weight and a linear live load of -10.00kN on FZ.

12.6 Verifying the cross section optimization according to EC3 (TTAD #11516)

Test ID: 3620

Test status: Passed

12.6.1 Description Verifies the cross section optimization of a steel element, according to Eurocodes 3.

Performs the finite elements calculation and the steel calculation. Generates the "Envelopes and shapes optimization" report.

The steel bar has a IPE360 cross section, a rigid hinge support at one end and a rigid support with translation restraints on X, Y and Z and rotation restraint on X. Two loads are applied: a punctual dead load of -1.00 kN on FZ and a punctual live load of -40.00 kN on FZ.

12.7 Verifying the shape sheet results for a column (TTAD #11550)

Test ID: 3640

Test status: Passed

12.7.1 Description Performs the finite elements calculation and the steel calculation. Generates the shape sheet report for a vertical steel element.

The steel element (S235 material, IPE300 cross section) has a rigid fixed support. A vertical live load of -200.00 kN is applied.

12.8 Verifying the shape sheet results for a fixed horizontal beam (TTAD #11545)

Test ID: 3641

Test status: Passed

12.8.1 Description Performs the finite elements calculation and the steel calculation. Generates the shape sheet report for a horizontal steel element, verifies the cross section class.

The steel element (S235 material, IPE300 cross section) has a rigid fixed support at one end and a rigid support with translation restraints on Y and Z and rotation restraint on X at the other end. A linear live load of -10.00 kN on FX and a punctual live load of 1000 kN on FX are applied.


374

12.9 CM66: Verifying the buckling length for a steel portal frame, using the kA kB method

Test ID: 3813

Test status: Passed

12.9.1 Description Verifies the buckling length for a steel portal frame with one level, using the kA kB method, according to CM66.

Generates the "Buckling and lateral-torsional buckling lengths" report.

12.10 CM66: Verifying the buckling length for a steel portal frame, using the roA roB method

Test ID: 3814

Test status: Passed

12.10.1 Description Verifies the buckling length for a steel portal frame with one level, using the roA roB method, according to CM66.


12.11 EC3: Verifying the buckling length for a steel portal frame, using the kA kB method

Test ID: 3819

Test status: Passed

12.11.1 Description Verifies the buckling length for a steel portal frame, using the kA kB method, according to Eurocodes 3.


12.12 Verifying the steel shape optimization when using sections from Advance Steel Profiles database (TTAD #11873)

Test ID: 4289

Test status: Passed

12.12.1 Description Verifies the steel shape optimization when using sections from Advance Steel Profiles database. Performs the finite elements calculation and the steel elements calculation and generates the steel shapes report.

The structure consists of columns with UKC152x152x23 cross section, beams with UKB254x102x22 cross section and roof beams with UKB127x76x13 cross section. Dead loads and live loads are applied on the structure.


375

12.13 Verifying the buckling coefficient Xy on a class 2 section

Test ID: 4443

Test status: Passed

12.13.1 Description Performs the finite elements calculation and the steel elements calculation. Verifies the buckling coefficient Xy on a class 2 section and generates the shape sheets report.

The model consists of a vertical linear element (I26*0.71+15*1.07 cross section and S275 material) with a rigid hinge support at the base and a rigid support with translation restraints on X and Y and rotation restraint on Z, at the top. A punctual live load is applied.

12.14 EC3: Verifying the buckling length results (TTAD #11550)

Test ID: 4481

Test status: Passed

12.14.1 Description Performs the steel calculation and verifies the buckling length results according to Eurocodes 3 - French standards. The shape sheet report is generated.

The model consists of a vertical linear element (IPE300 cross section, S275 material) with a rigid fixed support at the base. A punctual live load of 200.00 kN is applied.

12.15 EC3 fire verification: Verifying the work ratios after performing an optimization for steel profiles (TTAD #11975)

Test ID: 4484

Test status: Passed

12.15.1 Description Runs the Steel elements verification and generates the "Envelopes and optimizing profiles" report in order to check the work ratios. The verification is done by using the EC3 norm with Romanian annex.

12.16 Verifying the "Shape sheet" command for elements which were excluded from the specialized calculation (TTAD #12389)

Test ID: 4529

Test status: Passed

12.16.1 Description Verifies the program behavior when the "Shape sheet" command is used for elements which were excluded from the specialized calculation (chords).


376

12.17 Changing the steel design template for a linear element (TTAD #12491)

Test ID: 4540

Test status: Passed

12.17.1 Description Selects a different design template for steel linear elements.

12.18 Verifying the shape sheet for a steel beam with circular cross-section (TTAD #12533)

Test ID: 4549

Test status: Passed

12.18.1 Description Verifies the shape sheet for a steel beam with circular cross-section when the lateral torsional buckling is computed and when it is not.

13 Timber Design


378

13.1 Modifying the "Design experts" properties for timber linear elements (TTAD #12259)

Test ID: 4509

Test status: Passed

13.1.1 Description Defines the "Design experts" properties for a timber linear element, in a model created with a previous version of the program.

13.2 Verifying the timber elements shape sheet (TTAD #12337)

Test ID: 4538

Test status: Passed

13.2.1 Description Verifies the timber elements shape sheet.

13.3 Verifying the units display in the timber shape sheet (TTAD #12445)

Test ID: 4539

Test status: Passed

13.3.1 Description Verifies the Afi units display in the timber shape sheet.

14 XML Template Files


380

14.1 Saving the properties of a linear element as a template (DEV2012 #1.4)

Test ID: 4169

Test status: Passed

14.1.1 Description Saves the properties of a linear element as an XML file which can be later used as a template for other linear elements.

14.2 Saving the properties of a planar element as a template (DEV2012 #1.4)

Test ID: 4176

Test status: Passed

14.2.1 Description Saves the properties of a planar element as an XML file which can be later used as a template for other planar elements.

14.3 Loading a template with the properties of a linear element (DEV2012 #1.4)

Test ID: 4207

Test status: Passed

14.3.1 Description Loads an XML file as a properties template and applies it on a linear element. Saves the properties of the element on which the template was applied, in order to compare the files.

14.4 Loading a template with the properties of a planar element (DEV2012 #1.4)

Test ID: 4344

Test status: Passed

14.4.1 Description Loads an XML file as a properties template and applies it on a planar element. Saves the properties of the element on which the template was applied, in order to compare the files.

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