volume i on-orbit assembly, modeling, and mass properties...

JSC 26557 REVISION P VOLUME I

LESC 31166 REVISION P VOLUME I

On-Orbit Assembly, Modeling, and Mass Properties Data Book

Volume I International Space Station Program

June 2002

National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas



This page included for formatting purposes.



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VOLUMES I AND II This revision of the Data Book was segmented into two volumes due to the document size and because of a smaller customer base requiring data in Volume II. Volume I contains free flying and Orbiter-attached configuration properties necessary to fulfill the requirements of the ISS Technical Task Agreement JT-33. In Volume II the mass property and aerodynamic data are organized into a multi-body system utilized by analysts. Volume II provides data used by a limited number of customers within the ISS analysis community.



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INTERNATIONAL SPACE STATION

ON-ORBIT ASSEMBLY, MODELING, AND MASS PROPERTIES

DATA BOOK

PREFACE

This document was constructed using the March 2002 NASA approved Configuration List.

The contents of this document are to be consistent with the tasks and products prepared by the International Space Station Program (ISSP) participants as specified in Space Shuttle Program (SSP) 50011-01, Concept of Operation and Utilization, Volume I: Principles and SSP 50200-02, Station Program Implementation Plan, Volume II, Program Planning and Manifesting.



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DATA BOOK

CONCURRENCE

JUNE 2002

PREPARED BY:

System Engineering Modeling and Design Analysis (SEMDA) Laboratory Team

LOCKHEED MARTIN

ORG SUPERVISED BY:

JEROME D. POSEY

LOCKHEED MARTIN

PROJECT MANAGER – ADVANCED ENGINEERING ORG

SIGNATURE DATE APPROVED BY:

J. SEGUN THOMAS

LOCKHEED MARTIN

ACTIVITY MANAGER – ADVANCED ENGINEERING ORG


THOMAS L. FARRELL

NASA EA4

SYSTEMS ENGINEERING OFFICE ORG


IRENE M. PIATEK

NASA EA4

SYSTEMS ENGINEERING OFFICE ORG

SIGNATURE DATE

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LESC-31166 REVISION P VOLUME I

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DATA BOOK

LIST OF CHANGES

JUNE 2002

Data Book Entry Date Change Paragraphs

VOLUME I Revision P

JUNE 2002 Baseline All

VOLUME ll Revision P

JUNE 2002 Baseline All



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TABLE OF CONTENTS VOLUME I

SECTION PAGE LIST OF CONFIGURATIONS ....................................................................................xii 1.0 INTRODUCTION.......................................................................................... 1-1 1.2 SCOPE OF DOCUMENT............................................................................. 1-3 1.3 PRECEDENCE ............................................................................................ 1-3 1.4 CUSTOMER SUPPORT .............................................................................. 1-4 1.5 SOFTWARE TOOLS.................................................................................... 1-5 1.6 DISCLAIMER ............................................................................................... 1-7

2.0 DOCUMENTATION .................................................................................... 2-1 2.1 APPLICABLE DOCUMENTS ....................................................................... 2-1 2.2 CHANGES TO DATA BOOK FORMAT........................................................ 2-3

3.0 COORDINATE SYSTEMS ........................................................................... 3-1 3.1 LOCAL VERTICAL-LOCAL HORIZONTAL.................................................. 3-1 3.2 SPACE STATION ANALYSIS COORDINATE SYSTEM ............................. 3-1 3.3 ORBITER STRUCTURAL REFERENCE SYSTEM ..................................... 3-1 3.4 PRINCIPAL AXES........................................................................................ 3-5 3.5 RSA ANALYSIS COORDINATE SYSTEM................................................... 3-5 3.6 INFORMATION REPORTING...................................................................... 3-5 4.0 CONFIGURATION LIST............................................................................... 4-1

5.0 MASS DATA INTEGRATION....................................................................... 5-1 5.1 MASS PROPERTIES SOURCES ................................................................ 5-1 5.2 MASSES OF FREE FLYING CONFIGURATIONS ...................................... 5-1 5.4 MASSES OF ORBITER ATTACHED CONFIGURATIONS........................ 5-15 5.5 MASS PROPERTIES OF CORE COMPONENTS ..................................... 5-15

6.0 GEOMETRY DATA INTEGRATION............................................................. 6-1 6.1 ISS GEOMETRY.......................................................................................... 6-1 6.2 ORBITER GEOMETRY................................................................................ 6-1 6.3 ORBITER TO ISS ATTACH POINTS........................................................... 6-2

7.0 CONFIGURATION DATA............................................................................. 7-1 7.1 SECTION TITLE .......................................................................................... 7-1 7.2 CONFIGURATION DESCRIPTION.............................................................. 7-1 7.3 ELEMENT INTERFACES............................................................................. 7-2 7.4 ORBITER ATTACH POINT LOCATION....................................................... 7-2 7.5 ELEMENT PROPERTIES ............................................................................ 7-2 7.6 ILLUSTRATIONS AND CONFIGURATION MASS PROPERTIES .............. 7-2 7.7 MASS PROPERTIES FOR ORBITER AT BEGINNING, DURING, AND

END OF MATED OPERATIONS.................................................................. 7-4 7.8 AERODYNAMICS ........................................................................................ 7-4 7.9 CONFIGURATION DATA SECTIONS ......................................................... 7-5



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TABLE OF CONTENTS (CONTINUED) VOLUME I

SECTION PAGE APPENDIX A ACRONYMS AND ABBREVIATIONS ..................................... A-1 APPENDIX B COMPONENT DEFINITIONS ................................................. B-1 APPENDIX C DATA BOOK SPECIFICATIONS............................................. C-1 APPENDIX D Solar Array and SARJ Rotational Conventions ....................... D-1 APPENDIX E Worksite Naming Conventions ................................................ E-1

TABLE OF FIGURES VOLUME I

FIGURE PAGE

Figure 3.1-1 LVLH Frame........................................................................................ 3-2 Figure 3.2-1 SSACS Frame..................................................................................... 3-3 Figure 3.3-1 OSRS Frame....................................................................................... 3-4 Figure 3.5-1 RSA Analysis Coordinate System ....................................................... 3-6 Figure D-1 US Solar Array Conventions Phase 1 Complete……………………...... D-1 Figure D-2 US Segment Solar Array & Radiator Conventions Assembly Complete .......................................... D-2

TABLE OF TABLES VOLUME I

TABLE PAGE Table 4.0-1 Configuration List.................................................................................. 4-3 Table 5.2-1 Mass Summary of Free Flying Configurations...................................... 5-3 Table 5.3-1 SODB – Derived Orbiter Mass Properties ............................................ 5-9 Table 5.3-2 Generic Orbiter Mass Properties ........................................................ 5-13 Table 6.3-1 Orbiter to ISS Attach Points.................................................................. 6-2 Table E-1 Naming Convention for the MT Worksites……………………………… E-1


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TABLE OF CONTENTS

VOLUME II SECTION PAGE LIST OF CONFIGURATIONS ....................................................................................xii 8.0 BODY PROPERTIES......................................................................................... 8-1 APPENDIX A ACRONYMS AND ABBREVIATIONS................................................A-1 APPENDIX B COMPONENT DEFINITIONS............................................................B-1 APPENDIX C DATA BOOK SPECIFICATIONS...................................................... C-1

TABLE OF TABLES VOLUME II

TABLES PAGE Table 8.0-1 Body Pivot Point Locations.................................................................... 8-3 Table 8.0-2 Docking Locations for Soyuz and Progress Vehicles ............................ 8-4

TABLE OF FIGURES VOLUME II

FIGURES PAGE Figure 8.0-1 The Twenty-Eight Body System........................................................... 8-5

JSC 26557 REVISION P VOLUME

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LIST OF CONFIGURATIONS

CONFIGURATION 053 .................7-6 CONFIGURATION 070 ...............7-55 CONFIGURATION 071 ...............7-59 CONFIGURATION 076 .............7-107 CONFIGURATION 077 .............7-111 CONFIGURATION 078 ...............7-63 CONFIGURATION 079 ...............7-69 CONFIGURATION 080 ...............7-83 CONFIGURATION 081 ...............7-89 CONFIGURATION 082 ...............7-95 CONFIGURATION 083 .............7-165 CONFIGURATION 084 .............7-169 CONFIGURATION 086 .................7-7 CONFIGURATION 087 .............7-115 CONFIGURATION 088 .............7-121 CONFIGURATION 089 .............7-127 CONFIGURATION 090 .............7-137 CONFIGURATION 091 .............7-181 CONFIGURATION 092 .............7-187 CONFIGURATION 093 .............7-199 CONFIGURATION 094 .............7-205 CONFIGURATION 095 .............7-211 CONFIGURATION 096 .............7-215 CONFIGURATION 097 .............7-219 CONFIGURATION 098 .............7-223 CONFIGURATION 099 .............7-227 CONFIGURATION 100 .............7-173 CONFIGURATION 101 .............7-177 CONFIGURATION 102 .............7-141 CONFIGURATION 103 .............7-147

CONFIGURATION 104 .............7-153 CONFIGURATION 105 .............7-161 CONFIGURATION 106 ...............7-99 CONFIGURATION 107 .............7-103 CONFIGURATION 108 ...............7-75 CONFIGURATION 109 .............7-193 CONFIGURATION 110 .............7-231 CONFIGURATION 111 .............7-237 CONFIGURATION 112 .............7-243 CONFIGURATION 113 .............7-251 CONFIGURATION 114 .............7-255 CONFIGURATION 115 .............7-259 CONFIGURATION 116 .............7-263 CONFIGURATION 117 .............7-269 CONFIGURATION 118 .............7-275 CONFIGURATION 119 .............7-285 CONFIGURATION 120 .............7-289 CONFIGURATION 121 .............7-293 CONFIGURATION 122 .............7-299 CONFIGURATION 123 .............7-305 CONFIGURATION 124 .............7-311 CONFIGURATION 125 .............7-319 CONFIGURATION 126 .............7-323 CONFIGURATION 127 .............7-329 CONFIGURATION 128 .............7-335 CONFIGURATION 129 .............7-341 CONFIGURATION 130 .............7-347 CONFIGURATION 131 .............7-355 CONFIGURATION 132 .............7-361



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1.0 INTRODUCTION

The International Space Station (ISS) On-Orbit Assembly, Modeling and Mass Properties Data Book provides a program approved, baseline representation of the ISS as modeled using the March 2002 NASA approved Configuration List. The Systems Engineering, Modeling, and Design Analysis (SEMDA) Laboratory of the Lockheed Martin Space Operations (LMSO) Company in Houston, Texas produces this document for the National Aeronautics and Space Administration (NASA) Systems Engineering Office [EA4] at the Lyndon B. Johnson Space Center (JSC). SEMDA lab performs the design, development, testing and engineering portions of this work under ISS Technical Task JT-33, Assembly Analysis. The JT-33 is a subset of JT-156, EA Mission Compatibility/Assembly Analysis. Related sustaining engineering work is performed under the JSC-EA-2 Operations Analysis/Configuration Modeling Technical Task.

ISS geometry, mass properties, and on-orbit orientation information was collected from multiple sources, including NASA, Canadian Space Agency (CSA), European Space Agency (ESA), Japanese National Space Development Agency (NASDA), Russian Space Agency (RSA), Rocket Space Corporation – Energia (RSC-E), Khrunichev State Research and Production Space Center (KhSC), and Boeing. This information was used to create solid model representations of ISS hardware in a computer aided engineering package. These computer-generated solid model components were then organized into 58 configurations. These configurations represent stages from the post-Stage 3S After Separation on-orbit ISS to Stage 13A.1 After Separation. The ISS Mission Integration and the Vehicle Integrated Performance and Resources (VIPeR) team agreed to model and process the ISS Missions and operations from Stage 3S After Separation, which was current at the start of the data book construction period, through the next 18 months of assembly operations. This range was chosen to meet Design and Verification Analysis Cycle (VAC) commitments while minimizing rework due to uncertainties in the ISS assembly sequence and manifest. Construction of two data books per year was scheduled to address assembly sequence modifications affecting missions close to launch.

1.1 PURPOSE OF DATA BOOK

This Data Book provides comprehensive assembly and mass and aerodynamic properties data for the full range of the ISS construction activities with the following information provided for each configuration:

1) Detailed description

2) Solid model isometric illustration

3) Total ISS on-orbit mass



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4) Center of mass location

5) Inertia tensor*

6) Principal moments of inertia

7) Principal to body Euler rotation angles

8) Projected areas

9) Center of pressure offset matrix.

Configurations can contain other extra data sets as described in detail in Section 7.0 Configuration Data, including these items:

1) Element interfaces

2) Element properties*

3) Element dimensioned four-view drawings

4) Orbiter attach point location

5) Mass properties for an attached Orbiter vehicle*

6) Mass properties for mated ISS - Orbiter stack*

* Inertia matrix off-diagonal elements are negative integrals on these pages.



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1.2 SCOPE OF DOCUMENT

This document provides baseline ISS on-orbit body and configuration mass and aerodynamic properties for selected configurations, including Orbiter attached configurations. The SEMDA Lab provides this information to NASA, CSA, ESA, NASDA, RSA, RSC-E, KhSC, and Boeing personnel for analysis using the March 2002 NASA approved Configuration List, Table 4.0-1.

1.3 PRECEDENCE

Unless noted otherwise, information contained in this document will be consistent with ISSP and Mission Operations Directorate (MOD) documentation:

�� Assembly Matrix on the OM5 Assembly & Configuration Web Page (http://iss-www.jsc.nasa.gov/ss/issapt/assembly/assembly.html)

�� Mission specific Assembly Overview documents

When this Data Book conflicts with any ISS documents above concerning the ISS assembly and operational information, the documents listed above take precedence over the information contained in this document.

The body and configuration mass and aerodynamics properties data sets contained in this document take precedence over other ISS documentation with the exception of the following mission specific data resources:

�� Mass properties information for a specific Verification Analysis Cycle (VAC) for an upcoming flight. The VAC data will be generated using the Mass Properties Sustaining Engineering Tool (MPSET) prior to launch.

�� Mass properties information exchanged between NASA and RSC-E within 20 days of an on-orbit event, or series of events, for data synchronization purposes. These exchanges, defined in formal protocols, ensure that Mission Control-Moscow and Mission Control-Houston use consistent ISS mass properties data sets.

�� Validated SEMDA Lab data updates released between a Data Book delivery and a specified on-orbit event.



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1.4 CUSTOMER SUPPORT

Questions or comments regarding this document or corresponding ISS solid models may be directed to Mansour Falou/LMSO. Questions about mass properties used to generate data in this document may be directed to Oliver Philippi/LMSO.

Mansour Falou

Telephone: 281-333-6326

Facsimile: 281-333-6908

Mail Code: LMSO/C87

Electronic mail: [email protected]

Oliver Philippi

Telephone: 281-226-4881

Facsimile: 281-333-6908

Mail Code: LMSO/C87

Electronic mail: [email protected]

The SEMDA Lab team created the ISS data in this document. To obtain information pertaining to the contents, contact the individuals listed below via Mansour Falou.

Configuration Modeling: Dean Coleman Jeff Froemming

Brad Henry Theresa Tran

Mass Properties: Oliver Philippi Vera Annenkova

MODGEN: Mansour Falou

Documentation: Mansour Falou

Preparation: SEMDA Team



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Data from this document can be found electronically via these routes:

For users within the JSC domain, using a FTP utility: ftp address: seat2.jsc.nasa.gov

User name: anonymous

Password: [use electronic mail address]

Directory: change directory to “semda”

Note: the “semda” directory is hidden.

change directory to “iss-revp”

Using a browser such as Netscape or Internet Explorer:

ftp address: ftp://seat2.jsc.nasa.gov

This document can also be found at the SEMDA web page at:

WWW address: http://seat1.jsc.nasa.gov/semda

The “seat2” FTP server is no longer accessible by users who access it from outside the NASA/JSC domain. For those anonymous users, another FTP server was made available. Users can access it directly using a FTP utility:

ftp address: lmso.external.lmco.com/ User name: anonymous

Password: [use electronic mail address]

Or using a browser such as Netscape or Internet Explorer

ftp address: ftp://lmso.external.lmco.com/ Select the directory for data.

Work is underway to have links to all SEMDA products in the SEMDA web page. Users will be informed as these links and other improvements become available.

These servers are maintained as a courtesy to ISS data users. Contact Mansour Falou at 281-333-6326 for problems related to electronic data access.

1.5 SOFTWARE TOOLS

Four software tools were used to determine ISS mass and area properties:

ftp://seat2.jsc.nasa.gov/

http://seat1.jsc.nasa.gov/semda

ftp://lmso.external.lmco.com/



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1. Integrated Design Engineering Analysis Software (I-DEAS) Master Series Version 7m2;

2. stl_dump;

3. Universal Translator (UT);

4. MODel GENerator (MODGEN).



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I-DEAS is a commercial computer-aided engineering package of the Structural Dynamics Research Corporation (SDRC). In 1985 the Langley Space Station Office and the SDRC undertook development of a spacecraft analysis package entitled I-DEAS2. That software package was an integration of I-DEAS with a family of NASA analysis programs. The key conduit between I-DEAS and the programs was the MODGEN. The MODGEN converts a universal file, an I-DEAS output file, into a form usable by the programs. MODGEN also calculates properties. MODGEN was upgraded multiple times since 1985 by Structural Dynamics Research Corporation (SDRC) and LMSO. In 1993 SDRC released a completely re-architectured I-DEAS called I-DEAS Master Series. The previous architecture ended with I-DEAS VI. In 2001, Electronic Data Systems (EDS) purchased SDRC.

MODGEN and other SEMDA Lab supported software require I-DEAS VI universal files for input. Accordingly the SEMDA Lab developed software to recreate I-DEAS VI universal files from Master Series output. The principle software tools used were stl_dump and the UT.

The “stl_dump” program automatically generates stereolithography files in “STL” format of 3D Systems, Inc. The UT reads these and Master Series “archive” files to create I-DEAS VI universal files.

1.6 DISCLAIMER

Geometrical information contained in this document is included for general reference purposes to aid detailed analysis and operations planning activities.

Vehicle configurations and dimensions shown in this document are derived from data for static, on-orbit element configurations. Dynamic conditions due to applied loads, including internal pressure deformations of individual elements, and thermal effects are neither depicted nor dimensioned in this document. Detailed design, analysis, and operations planning tasks might need to incorporate on-orbit dynamic effects and deflections.

The SSP-ISS thermal control and proximity operations, plume impingement, structures, and flight control Joint Technical Working Groups (JTWG) should be consulted in determining on-orbit relative dynamic deflections and expected relative dimensions for specific vehicle or element components.

Dimensional tolerances used in this document are defined below. Users of this document are cautioned that dimensions and therefore tolerances, in this document are for General Reference Purposes Only!

Inches Millimeters

Linear Dimensions: ±3.0 ±76

Angular Dimensions: ±0.5°



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Or 10% of major dimensions whichever is less unless otherwise specified.

NOTE: No detailed design, manufacturing, or production data are included in this document or related electronic materials released for public access.



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2.0 DOCUMENTATION The following documentation, used in creation of this Data Book, is separated into categories for specific areas and sources of data.

2.1 APPLICABLE DOCUMENTS ISS Mass and Mass Properties [VIPeR and NASA]

�� Resource Analysis and Integration (RAI) Team, MIP Annex 1, Launch and Return Configurations - Payload Mass Properties Analyses. [February 2002]

�� Mass Properties Verification and Sustaining Engineering Tool (MPVSET), version 5.1 – Updated to include ISS Stage UF-1 Postflight Mass Properties Data.

Orbiter Mass Properties [NASA]

�� Shuttle Operational Data Book (SODB) National Space Transportation System (NSTS) 08934, Volume II, Amendments for Utilization Flight (UF) 2, 9A, Utilization Logistic Flight (ULF)1 and Flight 11A as released through April 2002.

Geometry [Boeing/NASA]

�� Boeing Physical Integration Team (PIT) electronic geometry files [March 2002] Geometry [Boeing PIT/CSA]

�� Electronic geometry files [March 2002] Geometry [Boeing PIT/ESA]

�� Electronic geometry files [December 1999] Orbiter Docking System (ODS) Androgynous Peripheral Attach System (APAS) Mating Geometry:

�� NSTS-21000-Interface Development Document (IDD)-ISS �� NSTS 07700, Volume X Geometry [RSA]

�� Video conference and facsimile communications with Russian engineers.

�� Periodic Technical Interchange Meeting (TIM) discussions [Coordinated with Boeing VIPeR and NASA ISS program officials]

�� Euclid and AutoCAD International Graphics Exchange Standard (IGES) software file transfers from Energia [October 1999]

�� EN-01 FGB Design Description Document Khrunichev State Research and Production Space Center (KhSC), Salyut Design Bureau [July 1998]

�� Research Program Office (RPO) 1342 Russian Soyuz-TM Technical Data Book, Revision C, Space Station Program Office [November 1998]

�� RPO-1551 Russian Service Module Technical Data Book, Basic, Space Station Program Office [December 20, 1996]



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�� RPO-2438 Russian Progress M1 Vehicle Technical Data Book, Preliminary Edition, Space Station Program Office [February 1998]

�� Description of Pirs DC 1, S. P. Korolev, Rocket Space Corporation “Energia” [March 31, 2000].

Coordinate Systems

�� SSP30219 ISS Reference Coordinate Systems Document, Revision E [November 29, 2000]

�� Solar Array Rotational Conventions http://viperweb.jsc.nasa.gov/mai/solarradiatororient.asp [December 1, 1999]

Assembly Sequences

�� D684-10514-2, Assembly Sequence and Manifest Document, Issue A, Draft 1 [February 7, 1994]

�� 4-18 Approved Assembly Sequence [April 18, 1994]

�� 6-30 Approved Assembly Sequence [June 30, 1994]

�� 9-28 Space Station Control Board (SSCB) Approved Assembly Sequence [September 28, 1994]

�� Design Analysis Cycle (DAC) 2 Post-Vehicle Integrated Product Team Preliminary Assembly Sequence [March 23, 1995]

�� ISS Assembly Sequence, Revision A [June 13, 1995]

�� Preliminary ISS Assembly Sequence, Revision B [April 15, 1996]

�� ISS Assembly Sequence, Revision B [September 26, 1996]

�� ISS Assembly Sequence, Revision C [September 4, 1997]

�� SSCB Approval [September 30, 1997]

�� ISS Assembly Sequence, Revision D [May 29, 1998]

�� ISS Assembly Sequence, Revision E [June 1, 1999]

�� Rev E, Design Change Notice (DCN)-04 [March 2000]

�� Interim ISS Assembly Sequence, Revision F-3 [December 2000]

�� Interim March 2001 Assembly Matrix

�� August 2001 Assembly Matrix [October 02, 2001]

�� March 2002 NASA approved configuration list

http://viperweb.jsc.nasa.gov/mai/solarradiatororient.asp



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2.2 CHANGES TO DATA BOOK FORMAT No baseline assembly sequence nor an assembly matrix after the August 2001 version and its October 2001 update were provided by the ISS program after Revision F-3. Since there were no assembly sequence nor assembly matrix to be used as the main reference in creating the Revision P Mass Properties Data Book, a NASA approved version of the Configuration List updated March 2002 is used as the main reference. Because of the lack of a baseline assembly sequence, the ISS program requested the omission of configuration dates. The latest assembly matrix and integrated flight schedule document can be found on the Assembly and Configuration web page at the following address:

http://iss-www.jsc.nasa.gov/ss/issapt/assembly/assembly.html



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3.0 COORDINATE SYSTEMS

The following sections define coordinate systems used in this document to describe ISS and Space Shuttle orientations.

3.1 LOCAL VERTICAL-LOCAL HORIZONTAL

The Local Vertical/Local Horizontal (LVLH) coordinate system, illustrated in Figure 3.1-1, is defined with the ZLO axis pointing to the nadir. The YLO axis points perpendicular to the orbital plane as a vector cross product of the radius and velocity vector. The XLO axis is the horizontal projection of the velocity vector, a vector cross product of the Y and Z unit vectors, that defines the local horizontal axis. The center of this right-handed orthogonal system is located at the vehicle center of mass.

3.2 SPACE STATION ANALYSIS COORDINATE SYSTEM

The Space Station Analysis Coordinate System (SSACS), illustrated in Figure 3.2-1, is a right-handed Cartesian, body-fixed coordinate system that corresponds to LVLH flight orientation. The origin is located at the geometric center of the mid-ship Integrated Truss Segment (ITS) S0. The longitudinal x-axis of multiple core modules, including the Zarya Functionalni Gruzvoi Blok (FGB) and Unity Node 1, is parallel with the analysis coordinate system axis XA, positive in the direction of the velocity vector. Positive YA axis runs parallel with the starboard truss from the center point at S0. Axis ZA completes the triad, pointing to the nadir.

3.3 ORBITER STRUCTURAL REFERENCE SYSTEM

The Orbiter Structural Reference System (OSRS), illustrated in Figure 3.3-1, is defined with the origin in the Orbiter plane of symmetry 400 inches below the center line of the payload bay and 236 inches forward of the Orbiter nose. The XO longitudinal axis runs parallel and 400 inches below the payload bay centerline, directed positive from the vehicle nose toward its tail. The vertical ZO axis resides in the vehicle plane of symmetry perpendicular to the XO axis and directed positive upward from the payload bay in the landing attitude. The YO axis completes the right-hand coordinate system, directed positive from the Orbiter centerline out to the tip of the starboard wing.

Figure 3.3-1 presents basic Orbiter dimensions and various positions of the ODS. The ODS provides an Orbiter docking interface with the ISS. The Orbiter side view indicates three extended ODS positions. The Fully Extended Position, Z=[479.76”], represents the maximum ODS interface extension limit. The Ready-To-Dock Position, Z=[475.51”], represents the standard ODS interface extension at first contact to the ISS docking interface. The Structural Lockup Position, Z=[460”], represents the ODS interface extension when the Orbiter securely docks to the ISS docking interface.



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Figure 3.1-1 LVLH Frame



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Figure 3.2-1 SSACS Frame



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The Orbiter top view indicates two ODS positions in the cargo bay. The ODS Aft position, X=[731.6”], was used for Space Transportation System (STS) -88, ISS Stage 2A, in 1998. The ODS Forward position, X=[649”], has been planned for use on all other Orbiter missions.

Figure 3.3-1 OSRS Frame



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3.4 PRINCIPAL AXES

Principal body axes coordinate systems are determined in this document for each ISS configuration and stage described. In each case, the origin of the principal axes coordinate system is located at the configuration center of mass. In the solution of the eigen value problem for identifying principal axes, principal moments of inertia are assigned in a manner to minimize rotations aligning ISS analysis coordinates and principal axes coordinates. The re-orientation of ISS axes from principal coordinate alignment to ISS analysis axis alignment uses a yaw-pitch-roll Euler angle sequence.

3.5 RSA ANALYSIS COORDINATE SYSTEM

This system, illustrated in Figure 3.5-1, is a right-handed Cartesian, body-fixed coordinate system. The origin is located at the center of the aft side of the aft Zvezda Service Module bulkhead. Coordinates of the RSA origin in the SSACS are [-35339, 4, 4139] millimeters. The x-axis, XR, is parallel to the x-axis of the SSACS but is positive in the opposite direction of the velocity vector. The positive y-axis, YR, runs parallel with the ZA axis, pointing zenith. The z-axis ZR, completes the triad.

3.6 INFORMATION REPORTING

Moments of inertia, products of inertia and centers of pressure reported in this document are given with respect to the specific element, body, or vehicle center of mass. The center of mass and other significant points are reported with respect to the SSACS frame, as defined in Section 3.2.

All configuration illustrations contain a Cartesian triad. The triad is not positioned at the vehicle center of mass. The triad indicates the orientation of the SSACS frame.

Aerodynamic centers of pressure are referenced in the SSACS frame to specific element, body, or vehicle center of mass and not the modeling origin.



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Figure 3.5-1 RSA Analysis Coordinate System



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4.0 CONFIGURATION LIST

The Configuration List contains 58 steps and their respective descriptions analyzed in this document. Selected configurations depict the ISS in a free flying mode, including before and after certain EVA tasks occur, or after selected vehicle movements take place. Each configuration type has a special designation. The names carry the designation of the space agency supplying the manifested cargo and the launch number associated with the specific deliverable. Configuration numbers are fixed to specific on-orbit events by NASA – RSA protocol in the months preceding an on-orbit event. Because of late sequence changes, configuration numbers might become non-sequential. Therefore, step numbers 1-58 have been introduced for this document. This procedure provides a sequential, continuous numbering scheme needed for certain analysts.

Examples include:

_After Rendezvous [ _AR ]

A stage configuration with the Orbiter attached, After Rendezvous

_Intermediate [ _INT ]

A stage configuration with the Orbiter attached, Intermediate

_Before Separation [ _BS ]

A stage configuration with the Orbiter attached, Before Separation

_After Separation [ _AS ]

A free flying configuration, After Separation of a Progress, Soyuz, or Orbiter

Note that a series flight number is often assigned to specific payloads for American (A) and Russian (R) assembly-build stages. Because the order that those payloads are manifested can change, the stages might not occur in numerical order for a given series. Thus, Stage 10A follows Stage 11A.

A American [NASA] assembly-build Space Shuttle Mission

P Progress [RSA] vehicle re-supply mission

R RSA launched assembly-build mission

S Soyuz [RSA] vehicle replacement mission

UF Utilization Flight [NASA] Space Shuttle Mission

ULF Utilization Logistic Flight [NASA] Space Shuttle Mission



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Table 4.0-1, applies information from various sources to organize model configuration assemblies.



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Table 4.0-1 Configuration List

Configuration Number

Revision P Step

Number Configuration / Step

Name Description

- - 1A/R Zarya FGB module launch.

- - 2A STS-88 Orbiter carried Unity Node 1, PMA 1 and PMA 2 assembly which was attached to Zarya FGB forward.

001 - STAGE 2A.1 ISS after STS-96 Orbiter separation and reboost activities. 002 - STAGE 2A.2A_AR ISS with STS-101 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA 2. 003 - STAGE 2A.2A_BS ISS with STS-101 Orbiter before separation [fully unloaded].

004 - STAGE 2A.2A_AS ISS after STS-101 separation following logistics and outfitting transfers with Zarya FGB and Unity Node 1. Assemble and move Strela Cargo Boom-2 from PMA 2 to PMA 1.

005 - STAGE 1R ISS with Zvezda Service Module after docking to Zarya FGB aft. 006 - FLIGHT 1P ISS with 1P Progress M1-3 after docking to Zvezda Service Module aft. 007 - STAGE 2A.2B_AR ISS with STS-106 Orbiter after rendezvous [fully loaded] to PMA 2.

008 - STAGE 2A.2B_BS ISS with STS-106 Orbiter before separation [fully unloaded]; Extravehicular Activity (EVA)s completed.

009 - STAGE 2A.2B_AS ISS after STS-106 Orbiter separation following logistics and outfitting transfers with Zarya FGB, Unity Node 1, Zvezda Service Module, and 1P Progress.

011 - STAGE 3A_AR ISS with STS-92 Orbiter after rendezvous [fully loaded] to PMA 2.

012 - STAGE 3A_INT ISS with STS-92 Orbiter after ITS Zenith 1 (Z1) berthed to Unity Node 1 zenith Common Berthing Mechanism (CBM). Z1-mounted Space to Ground Antenna (SGANT), know as the Ku-band Antenna, remains stowed.

013 - STAGE 3A_BS

ISS with STS-92 Orbiter before separation [fully unloaded]. Relocate S-band Antenna Structural Assembly (SASA) and Direct Current-to-Direct Current Converter Units (DDCUs) and install Ku-band Antenna Z1. Berth PMA 3 to Unity Node 1 nadir CBM. Deploy Z1 utility tray; Relocate grapple fixture and keel pin.

014 - STAGE 3A_AS ISS after STS-92 Orbiter separation. 015 - FLIGHT 1P_AS ISS after 1P Progress M1-3 separation from Zvezda Service Module aft.

016 - FLIGHT 2R_AR1 ISS with 2R Soyuz TM-31 after docking to Zvezda Service Module aft. 2R Soyuz carried the first ISS crew.

010 - FLIGHT 2P_AR ISS with 2P Progress M1 after docking to Zarya FGB nadir.

017 - FLIGHT 2P_AS ISS after 2P Progress M1 separation from Zarya FGB nadir following unloading of propellant and dry cargo, and loading of waste.

018 - STAGE 4A_AR ISS with STS-97 Orbiter after rendezvous [fully loaded].



4-4


Revision P Step


Name Description

019 - STAGE 4A_INT1 ISS with STS-97 Orbiter with ITS Port 6 (P6) held in the parking position. Solar arrays and radiators remain stowed in launch position.

020 - STAGE 4A_INT2 ISS with STS-97 Orbiter after ITS P6 attached to Z1 truss zenith. Solar arrays and radiators remain stowed in launch position.

021 - STAGE 4A_BS ISS with STS-97 Orbiter before separation. Rotate P6 keel pin; Deploy P6 solar arrays and forward radiator. Relocate S-band Antenna from Z1 to P6 zenith. Deploy P6 aft radiator, deploy EVA Bag on P6; deploy Plasma Probe to P6 aft zenith surface.

022 - STAGE 4A_AS ISS after STS-97 Orbiter separation. 023 - FLIGHT 2P_AR2 ISS with 2P Progress M1 after docking to Zvezda Service Module aft. 024 - FLIGHT 2P_AS2 ISS after 2P Progress M1 separation from Zvezda Service Module aft. 025 - STAGE 5A_AR ISS with STS-98 Orbiter after rendezvous [fully loaded]. 026 - STAGE 5A_INT1 ISS with STS-98 Orbiter after PMA 2 moved to Z1 forward [rotated 102 degrees].

027 - STAGE 5A_INT2 ISS with STS-98 Orbiter after Destiny Lab berthed to Unity Node 1 forward CBM. Deploy P6 starboard radiator. Remove Ku-band Antenna gimbal locks. Install Lab Power and Data Grapple Fixture (PDGF) and window shutter gearbox.

028 - STAGE 5A_BS ISS with STS-98 Orbiter [fully unloaded] before separation. PMA 2 moved from Z1 forward to Destiny Lab forward CBM, S-band spare on Z1.

029 - STAGE 5A_AS ISS after STS-98 Orbiter separation.

030 - FLIGHT 2R_AR2 ISS with 2R Soyuz TM-31 after docking to Zarya FGB nadir. 2R Soyuz relocated from Zvezda Service Module aft to Zarya FGB nadir.

031 - FLIGHT 3P_AR ISS with 3P Progress M-44 after dockeding to Service Module aft. 032 - STAGE 5A.1_AR ISS with STS-102 Orbiter after rendezvous [fully loaded].

033 - STAGE 5A.1_INT1 ISS with STS-102 Orbiter after portside Early Communications (ECOMM) Antenna removed and stowed inside Unity Node 1. Install Lab Cradle Assembly (LCA) and PDGF Rigid Umbilical. PMA 3 moved to Unity port CBM. Berth Leonardo Multi-Purpose Logistics Module (MPLM) to Unity nadir.

034 - STAGE 5A.1_INT2 ISS with STS-102 Orbiter after External Stowage Platform (ESP) and one Pump and Flow Control Subassembly (PFCS) installed on Destiny Lab forward. Before unloaded Leonardo off Unity Node 1 nadir.

035 - STAGE 5A.1_BS ISS with STS-102 Orbiter before separation with MPLM returned, EVAs complete. 036 - STAGE 5A.1_AS ISS after STS-102 Orbiter separation.

038 - FLIGHT 3P_AS ISS after 3P Progress M-44 separation from Zvezda Service Module aft following unloading of propellant and dry cargo, and loading of waste.



4-5


Revision P Step


Name Description

030d - FLIGHT 2R_AR3 ISS with 2R Soyuz TM-31 after docking to Zvezda Service Module aft. Relocate 2R Soyuz from Zarya FGB nadir to Zvezda Service Module aft.

040 - STAGE 6A_AR ISS with STS-100 Orbiter after rendezvous [fully loaded].

041 - STAGE 6A_INT1 ISS with STS-100 Orbiter after Launch Deploy Assembly (LDA) mechanism secures Spacelab Pallet (SLP) to LCA.

042 - STAGE 6A_INT2 ISS with STS-100 Orbiter with Ultra High Frequency (UHF) Antenna deployed and attach Space Station Remote Manipulator System (SSRMS) to Destiny Lab PDGF. Install fully loaded Raffaello MPLM on Unity Node 1 nadir.

043 - STAGE 6A_INT3 ISS with STS-100 Orbiter before SLP off Destiny Lab. Remove Starboard ECOMM antenna and stowed in Unity. Install DC Switching Unit (DCSU) on ESP.

044 - STAGE 6A_INT4 ISS with STS-100 with SLP returned to payload bay by the SSRMS. Before the unloaded Raffaello MPLM removed from Unity Node 1 nadir.

045 - STAGE 6A_BS ISS with STS-100 Orbiter before separation with MPLM returned. EVAs completed. 046 - STAGE 6A_AS ISS after STS-100 Orbiter separation.

047 - FLIGHT 2S_AR1 ISS with 2S Soyuz TM-32 after docking to FGB nadir. Soyuz clocked at 45. Prior to this configuration, SM Transfer Docking Cone was relocated to SM nadir port.

048 - FLIGHT 2R_AS3 ISS after 2R Soyuz TM-31 separation from Service Module aft. 039 - FLIGHT 4P_AR ISS with 4P Progress M1-6 after docking to Zvezda Service Module aft. 049 - STAGE 7A_AR ISS with STS-104 Orbiter after rendezvous [fully loaded]. 050 - STAGE 7A_INT1 ISS with STS-104 Orbiter after Airlock module berthed to Node 1 starboard CBM.

051 - STAGE 7A_INT2 ISS with STS-104 Orbiter after installation of one O2 and one N2 High Pressure Gas Assembly (HPGA) units on the Airlock.

052 - STAGE 7A_BS ISS with STS-104 Orbiter before separation [fully unloaded]. Install Remaining HPGA assembly units.

053 - STAGE 7A_AS ISS after STS-104 Orbiter separation. ISS PHASE 2 COMPLETE

054 - STAGE 7A.1_AR ISS with STS-105 Orbiter after rendezvous [fully loaded].

055 - STAGE 7A.1_INT1 ISS with STS-105 Orbiter after fully loaded Donatello MPLM berthed to Unity Node 1 nadir.



4-6


Revision P Step


Name Description

056 - STAGE 7A.1_INT2

ISS with STS-105 Orbiter after Articulating Portable Foot Restraint (APFR) installed. Install Early Amonia Servicer (EAS) on P6 truss forward trunnion. Install external attached Payload 1 A and B Materials ISS Experiment (MISSE) on Airlock nadir center High Pressure Gas Tank (HPGT) (#2) and crew lock. Donatello MPLM unloaded, but still on Unity Node 1 nadir. Install Flight 8A and S0 truss LTA cables.

057 - STAGE 7A.1_BS ISS with STS-105 Orbiter before separation and with MPLM returned. 058 - STAGE 7A.1_AS ISS after STS-105 Orbiter separation.

058c - FLIGHT 4P_AS ISS after 4P Progress M1-6 separation from Zvezda Service Module aft, following unloading of propellant and dry cargo, loading of waste.

058g - FLIGHT 5P_AR ISS with 5P Progress M-45 after docking to Zvezda Service Module aft. 5P carrying the Russian experiment Micro-Particle Capture (MPAC) / Space Environment Exposure Devices (SEEDS).

037 - STAGE 4R_AR ISS with Docking Compartment (DC) 1 after docking to Zvezda Service Module nadir. Second Strela Cargo Boom (Strela-1) launched inside DC 1. Universal Instrument Section (UIS) attached to DC 1 nadir.

069 - FLIGHT 2S_AS1

ISS after 2S Soyuz TM-32 separation from Zarya FGB nadir. Prior to this configuration, an EVA occurs in which the UIS detaches from DC1. Deploy Soyuz docking target on DC1 nadir. Deploy MPAC /SEEDS experiment on SM port nadir handrails. EVA egress ladder is installed on DC1 EVA hatch, and deploy Strela 1 on DC1 starboard side. Install and deploy Boom with antenna on DC1 nadir.

69e - FLIGHT 2S_AR2 ISS with 2S Soyuz TM-32 after docking to DC1. This maneauver is required to ensure that 3S can dock to FGB nadir port to support the Orlan based EVA from DC1.

068 - FLIGHT 3S_AR ISS with 3S Soyuz TM-33 after docking to FGB nadir. Soyuz clocked 45 deg. 069h - FLIGHT 2S_AS2 ISS after 2S Soyuz TM-32 separation from DC1.

059 - FLIGHT 5P_AS ISS after 5P Progress M-45 separation from Zvezda Service Module aft. After unloading of propellant and dry cargo; loading waste.

060 - FLIGHT 6P_AR ISS with 6P Progress M1-7 after docking to Zvezda Service Module aft.

063 - STAGE UF1_AR ISS with STS-108 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir.

064 - STAGE UF1_INT1 ISS with STS-108 Orbiter after fully loaded MPLM berthed to Unity Node 1 nadir port. 065 - STAGE UF1_INT2 ISS with STS-108 Orbiter. MPLM is prepared for return, but still attached to Node 1. 066 - STAGE UF1_BS ISS with STS-108 Orbiter before separation with MPLM returned. 067 - STAGE UF1_AS ISS after STS-108 Orbiter separation.



4-7


Revision P Step


Name Description

061 - FLIGHT 6P_AS

ISS after 6P Progress M1-7 separation from Zvezda Service Module aft after unloading of propellant and dry cargo and loading of waste. Prior to this configuration, relocate Strela 2 from PMA-1 to DC1. Install 2 ISS Ham Radio Antennas WA3 and WA4 on SM handrails 2627 and 2642, respectively. Relocate Russian Strela Grapple Fixture to FGB EFGF, and remove US Grapple Fixture Adapter from PMA-1.

062 - FLIGHT 7P_AR ISS with 7P Progress M1-8 after docking to Zvezda Service Module aft.

072 - STAGE 8A_AR ISS with STS-110 Orbiter after rendezvous [fully loaded]. Orbiter Docked to PMA-2 tail nadir.

073 - STAGE 8A_INT1 ISS with STS-110 Orbiter after SSRMS berths ITS S0, with Mobile Transporter (MT), to LCA on United States Laboratory (Destiny Lab) zenith. Install the forward and aft S0 truss MTS struts to the Destiny Lab. (Note: Fwd and Aft struts are performed on two separate EVAs)

074 - STAGE 8A_BS

ISS with STS-110 Orbiter before separation. Install and deploy the Lab starboard and port avionics umbilical trays and connect umbilicals. Deploy S0-to-Lab aft trays and connect umbilicals. Install Airlock spur between the Airlock and S0 truss. Deploy Extravehicular-Charged Particle Detection System (EV-CPDS). Install Crew and Equipment Translation Assembly (CETA) light on Destiny Lab. Install Node 1 port CETA lights. Install S0-to-Node 1 tray and connect umbilicals. Install starboard and port CETA-to-MT energy absorber. Install S0 PWP and relocate MT from launch position to worksite #4. Remove and stow keel pins. Deploy Node 1 swing arm.

075 - STAGE 8A_AS ISS after STS-110 Orbiter separation. 085 - FLIGHT 4S_AR1 ISS with 4S Soyuz TM-34 after docking to DC1.

Beginning of 18 month analysis window for Data Book revision P 086 001 FLIGHT 3S_AS ISS after 3S Soyuz TM-33 separation from Zarya FGB nadir port.

070 002 FLIGHT 7P_AS ISS after separation of 7P Progress M1-8 from Zvezda Service Module aft, after unloading of propellant and dry cargo and loading waste.

071 003 FLIGHT 8P_AR ISS with 8P Progress M-46 after docking to Zvezda Service Module aft.

078 004 STAGE UF2_AR ISS with STS-111 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir.

079 005 STAGE UF2_INT1 ISS with STS-111 Orbiter after fully loaded MPLM berthed to Unity Node 1 nadir.

108 006 STAGE UF2_INT2 ISS with STS-111 Orbiter after PDGF is installed on P6 truss and Service Module Debris Panel (SMDP) kit stowed on PMA-1.



4-8


Revision P Step


Name Description

080 007 STAGE UF2_INT3 ISS with STS-111 Orbiter after MBS installed on the MT and the MBS Latching End Effector (LEE) and MBS camera deployed. MPLM is prepared for return, but still attached to Node 1.

081 008 STAGE UF2_BS ISS with STS-111 Orbiter before separation. Return MPLM returned to Orbiter bay. EVA activities completed.

082 009 STAGE UF2_AS ISS Stage UF2 after separation of STS-111 Orbiter.

106 010 FLIGHT 4S_AS1 ISS after 4S Soyuz TM-34 separation from DC1. Prior to this configuration, relocate SSRMS from Destiny Lab to MBS.

107 011 FLIGHT 4S_AR2 ISS with 4S Soyuz TM-34 after docking to Zarya FGB nadir port. Service Module Debris Panels (SMDP) and two Ham Radio Antennas installed on Service Module (SM)

076 012 FLIGHT 8P_AS ISS after 8P Progress M-46 separation from Zvezda Service Module aft, after unloading of propellant and dry cargo and loading of waste.

077 013 FLIGHT 9P_AR ISS with 9P Progress M1-9 after docking to Zvezda Service Module aft.

087 014 STAGE 9A_AR ISS with STS-112 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir. Prior to this configuration, relocate MT to worksite #5.

088 015 STAGE 9A_INT1 ISS with STS-112 Orbiter after ITS Starboard 1 (S1) berthed to S0.

089 016 STAGE 9A_BS

ISS with STS-112 Orbiter before separation. Install external cameras and stanchions on Destiny Lab [port 13] and S1 truss Outboard Lower [port 3]. Deploy S-band Antenna on S1. Deploy the External Active Thermal Control System (EATCS) S1 truss center radiator. Deploy CETA Cart A to starboard side of MT. Install and deploy CETA light stanchion and lights on S1 truss. Remove and stow S1 truss starboard and port keel pins. Relocate Tool Stanchion, Orbital Replacemnet Unit [ORU] Transfer Device (OTD) from PMA-1, and EVA Tool Stowage Device (ETSD) #2 starboard to CETA Cart A.

090 017 STAGE 9A_AS ISS after STS-112 Orbiter separation.

102 018 STAGE 11A_AR ISS with STS-113 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir. Prior to this configuration, relocate MT to worksite #5 and remove MPAC/SEEDS panel #1 and re-configure panels #2 and #3 on the MPAC/SEEDS support structure.

103 019 STAGE 11A_INT1 ISS with STS-113 Orbiter after ITS Port 1 (P1) berthed to S0.



4-9


Revision P Step


Name Description

104 020 STAGE 11A_BS

ISS with STS-113 Orbiter before separation. Install Wireless Video System [WVS] External Transceiver Assembly (WETA)s and stanchions on Node 1 [port 12] and P1 Outboard Upper [port 8]. Deploy EATCS P1 truss center radiator. Deploy and relocate CETA cart B to starboard side of MT. MT/CETA Cart configuration is MT-CETA-CETA. Remove and stow P1 truss starboard and port keel pins. Install APFR, tool stanchion and ETSD port on CETA Cart B. Deploy UHF antenna.

105 021 STAGE 11A_AS ISS after STS-113 Orbiter separation.

083 022 FLIGHT 9P_AS ISS after 9P Progress M1-9 separation from Zvezda Service Module aft, following unloading of propellant and dry cargo and loading of waste.

084 023 FLIGHT 10P_AR ISS with 10P Progress M-47 after docking to Zvezda Service Module aft. 100 024 FLIGHT 5S_AR ISS with 5S Soyuz TMA-1 after docking to DC 1 nadir. 101 025 FLIGHT 4S_AS2 ISS after 4S Soyuz TM-34 separation from FGB nadir.

091 026 STAGE ULF1_AR ISS with STS-114 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir. Prior to this configuration, relocate SSRMS from MBS to Destiny Lab.

092 027 STAGE ULF1_INT1 ISS with STS-114 Orbiter after ESP-2 with ORUs installed on A/L forward trunnions. Video Stanchion Support Assembly (VSSA) Flight Support Equipment (FSE) with two stanchion is stowed on ESP-2.

109 028 STAGE ULF1_INT2 ISS with STS-114 Orbiter after Fully loaded MPLM berthed to Node 1 nadir.

093 029 STAGE ULF1_INT3

ISS with STS-114 Orbiter after MPLM is prepared for return, but still attached to Node 1. Replace External Attached Payload 1 A and B (MISSE) on A/L nadir center HPGT (#2) and crew lock with External Attached Payload 1 C and D (MISSE). Install external camera and stanchion on P1 truss inboard lower [port 7]. Install Field Plasma Measurement Unit (FPMU) and stanchion on S1 truss outboard upper [port 2].

094 030 STAGE ULF1_BS ISS with STS-114 Orbiter before separation. Return MPLM to Orbiter bay. 095 031 STAGE ULF1_AS ISS after STS-114 separation.

096 032 FLIGHT 10P_AS ISS after 10P Progress M-47 separation from Zvezda Service Module aft. Prior to this configuration, the following activities are performed. Relocate SSRMS from Destiny Lab to MBS.

097 033 FLIGHT 11P_AR ISS with 11P Progress M1-10 after docking to Zvezda Service Module aft. 098 034 FLIGHT 11P_AS ISS after 11P Progress M1-10 separation from Zvezda Service Module aft. 099 035 FLIGHT 12P_AR ISS with 12P Progress M-48 after docking to Service Module aft.



4-10


Revision P Step


Name Description

110 036 STAGE 12A_AR ISS with STS-115 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir. Prior to this configuration, relocate MT to worksite #7. P6 solar arrays are fixed at 150/210 (2B/4B) degrees.

111 037 STAGE 12A_INT1 ISS with STS-115 Orbiter after ITS Port 3 and 4 (P3 and P4) are attached to P1 truss.


ISS with STS-115 Orbiter before separation. Rotate P4 truss keel pin. Remove and stow P3 truss keel pin. Rotate Solar Alpha Rotary Joint (SARJ) 180 deg to 0 deg position [launch and install position at 180 deg]. Deploy Channels 4A and 2A Solar Arrays. Deploy P4 truss Photovoltaic (PV) radiator. Relocate SASA from P6 to P1 and the BSP and Transponder from Z1 to P1. Install WETA and stanchion on P3 truss [port 10]; one stanchion remains on VSSA FSE on ESP-2. Relocate MT to worksite #4. Prior to separation, P6 solar array are fixed at 150/210 (2B/4B) degrees and P4 solar arrays will be fixed at 90/270 (2A/4A) degrees.

113 039 STAGE 12A_AS ISS after STS-115 separation. 114 040 FLIGHT 6S_AR ISS with 6S Soyuz TMA-2 vehicle after docking to FGB nadir. 115 041 FLIGHT 5S_AS ISS after 5S Soyuz TMA-1 separation from Pirs DC 1 nadir port.

116 042 STAGE 12A.1_AR ISS with STS-116 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir. Prior to this configuration, relocate MT to worksite #5. Port SARJ fixed at 0 degrees, P4 solar arrays fixed at 90/270 (2A/4A) degrees, and P6 beta gimbals fixed at 150/210 (2B/4B) degrees.

117 043 STAGE 12A.1_INT1 ISS with STS-116 Orbiter after ITS Port 5 (P5) berthed to P4 truss segment. Relocate MT to worksite #8.

118 044 STAGE 12A.1_BS

ISS with STS-116 Orbiter before separation. Relocate the Photovoltaic Removable Grapple Fixture (PVRGF) Orbital Support Equipment (OSE) to the MBS Latching End Effector (LEE). Deactivate and retract P6 truss Channel 4B Port Solar Array. Transfer the Pump Module and SHOSS Box (DDCU Cold Plate (CP), and Main Bus Switching Unit (MBSU) CP) to the ESP-2. Transfer the VSSA FSE from the ESP-2 to Integrated Cargo Carrier (ICC). Activate the first and second External Active Thermal Control System (EATCS) loops. Transfer the PFCS from ESP-1 to ICC. Relocate MT to worksite #4. CETA cart configuration is CETA-CETA-MT. Prior to separation, Port SARJ fixed at 90 degrees, P4 beta gimbals fixed at 290/70 (2A/4A) degrees, and P6 beta gimbals fixed at 150/210 (2B/4B) degrees.

119 045 STAGE 12A.1_AS ISS after STS-116 separation. 120 046 FLIGHT 12P_AS ISS after 11P Progress M1-10 separation from Zvezda Service Module aft.



4-11


Revision P Step


Name Description

121 047 FLIGHT 13P_AR ISS with 12P Progress M-48 after docking to Service Module aft. Prior to this configuration, retract and stow P6 starboard and aft Early External Active Thermal Control System (EEATCS) radiators. Transfer PVRGF from MBS LEE to P6 aft EEATCS radiator. Install Node 1 starboard CETA light.

122 048 STAGE 13A_AR ISS with STS-117 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir. Prior to this configuration, relocate MT to worksite #2. Port SARJ is fixed at 90 degrees and P4 beta gimbals are fixed at 290/70 (2A/4A) degrees.

123 049 STAGE 13A_INT1 ISS with STS-117 Orbiter after ITS Starboard Trusses 3 and 4 (S3 and S4) are attached to S1 truss.


ISS with STS-117 Orbiter before separation. Rotate S4 truss keel pin. Relocate P6 truss EEATCS aft radiator to S4 truss. Remove and stow S3 truss keel pin. Move PVRGF OSE from S4 truss radiator to MBS LEE. Retract P6 truss starboard Solar Array. Deploy S4 truss radiator. Deploy and activate Channel 1A and 3A Solar Array and connect to MBSU. Relocate MT to worksite #4. Prior to separation, the Port SARJ is fixed at 90 degrees, P4 beta gimbals is fixed at 290/70 (2A/4A) degrees, Starboard SARJ is fixed at 270 degrees, and S4 beta gimbals are fixed at 300/60 (1A/3A) degrees.

125 051 STAGE 13A_AS ISS after STS-117 separation.

126 052 STAGE 13A.1_AR

ISS with STS-118 Orbiter after rendezvous [fully loaded]. Orbiter docked to PMA-2 tail nadir. Prior to this configuration, relocate MT to worksite #3, retract P6 PV forward Radiator (PVR), and install S3 CETA light. Port SARJ is fixed at 90 degrees, P4 beta gimbals is fixed at 290/70 (2A/4A) degrees, Starboard SARJ is fixed at 270 degrees, S4 beta gimbals fixed at 300/60 (1A/3A) degrees.

127 053 STAGE 13A.1_INT1

ISS with STS-118 Orbiter after MT, with SSRMS carrying S5 and attached to MBS, translates from worksite #3 to worksite #1. SSRMS maneuvers S5 and berth it to S3/S4. CETA cart configuration is CETA-MT-CETA. S4 beta gimbals is fixed at 180 degrees and Starboard SARJ is fixed between 250 and 258 degrees for S5 installation.

128 054 STAGE 13A.1_INT2 ISS with STS-118 after MT is translated from worksite #1 to #4. Move EAS from P6 to ICC.

129 055 STAGE 13A.1_INT3 ISS with STS-118 after MT is translated from worksite #4 to worksite #8. P6 is moved to the overnight park position. A negative hold position for P6 is assumed based on a negative ISS beta orbit.

130 056 STAGE 13A.1_INT4 ISS with STS-118 after SSRMS berths P6 to MBS LEE, then SSRMS berth P6 to P5. Deploy P6 PV radiator.



4-12


Revision P Step


Name Description

131 057 STAGE 13A.1_BS

ISS with STS-118 Orbiter before separation. Deploy P6 channel 4B and channel 2B solar arrays. Translate MT from worksite #8 to worksite #4 (parked location). SSRMS is relocated from MBS to Destiny Lab. Prior to separation, Port SARJ is fixed at 90 degrees, P4 beta gimbals is fixed at 290/70 (2A/4A) degrees, Starboard SARJ is fixed at 270 degrees, S4 beta gimbals is fixed at 300/60 (1A/3A) degrees.

132 058 STAGE 13A.1_AS ISS after STS-118 separation. End of 18 month analysis window for Data Book revision P



5-1

5.0 MASS DATA INTEGRATION

Mass properties input data was supplied to the SEMDA Laboratory by the Lockheed Martin Resource, Analysis, and Integration (RAI) Team. Mass properties input data was integrated from a variety of sources using the MPVSET. Mass properties were entered into the I-DEAS Computer Aided Design (CAD) model when available. If only mass was provided, I-DEAS calculated mass properties assuming a uniform density.

5.1 MASS PROPERTIES SOURCES

Lockheed Martin (LM) RAI team and SEMDA team used a variety of sources to generate the mass properties input data for the I-DEAS CAD Model. The VIPeR Resource Management Mass Manifest spreadsheet provided equipment lists and launch weight tables consistent with Vehicle Management Data Book (VMDB) inputs. Cargo Element Mass Properties spreadsheets supplied mass properties from United States manufacturers and integrators. RSC-E supplied Progress and Soyuz vehicle mass properties. Space Shuttle data for Assembly and Logistics flights were obtained from SODBs. Refer to Section 2.1 for details.

5.2 MASSES OF FREE FLYING CONFIGURATIONS

Mass Summary of Free Flying Configurations, Table 5.2-1, provides data for ISS alone configurations with delta mass changes. During these configurations, the Orbiter mass is omitted from the ISS total mass. Table 5.2-1 provides step number, stage name and corresponding ISS components with associated masses manifested. ISS configurations with zero mass changes are omitted. Table 5.2-1 provides the following:

Step Number Sequential number of the flight.

Stage Name Number

Stage name or space agency launch designation or special designation for a significant ISS geometry modification

Element Description

Manifested components added to the ISS [or those orbiting items returning to Earth]

Mass [lb] Mass of payload components in pounds

Mass [kg] Mass of payload components in kilograms

Stage Total [kg] Net total mass of payloads to or from orbit by a configuration



5-2

Section 4.0 provides additional nomenclature explanations. Multiple ISS pressurized modules and other components change mass during ISS assembly. The repeated appearance of a component named in Table 5.2-1 addresses this effect. A suffix designates flight or range of flights for which the indicated mass applies. The Stage Total and Station Total column entries include only the net mass delta added to the ISS.



5-3

Table 5.2-1 Mass Summary of Free Flying Configurations

Step Name Component Description Mass Mass Stage Station

Number [lb] [kg] Total [kg] Total [kg] 3S_AS ISS Core - 3S_AS 240220 108962

001 Progress 7P (@ SM Aft) 15288 6934 Soyuz 4S (@ DC1 Nadir) 14871 6745 PMA-2 2565 1164 PMA-3 2575 1168

SM PV Array - Port 1279 580 SM PV Array - Starboard 1279 580

FGB PV Array - Port 551 250 FGB PV Array - Starboard 551 250 ITS P6 Core 23556 10685 P6 Beta Gimbal Assembly (Deployed) 1876 851 P6 POA Solar Array (Deployed) 2342 1062 P6 POF Solar Array (Deployed) 2335 1059 P6 Radiator (Deployed) 1612 731 Plasma Probe 85 39 S6 Radiator (Deployed) 1640 744 S4 Radiator (Deployed) 1640 744 S-Band Antenna (on ITS Z1) 227 103 S-Band Antenna (on ITS P6) 227 103

PFCS (on ESP-1) 488 221 DCSU (@ ESP on US Lab) 476 216

SSRMS 3311 1502 Mobile Transporter (on S0) 1826 828 PWP (on S0) 170 77 EVA System Tool Boxes (on Z1) 478 217 EV-CPDS 53 24 Early Ammonia Servicer 1433 650 DC-1 6533 2963 DC-1 Strela 1 383 174 DC-1 Strela 2 383 174 149799 149799

7P_AS ISS Core - 7P_AS 240059 108889 002 7P Progress (UNDOCKING) -15288 -6934 -7007 142792

8P_AR 8P Progress (DOCKING) 15287 6934 6934 149726

003

UF2_IN1 MPLM (Launch Configuration) berthed to Node 1 23029 10446 10446 160172005

UF2_IN2 SMDP 110 50

006 PDGF 73 33 83 160255

UF2_IN3 MBS installed on MT 3182 1443 1443 161698007

UF2_BS MPLM (Return Configuration) back into P/L Bay -23029 -10446 -10446 151252

008

4S_AS1 Soyuz 4S (UNDOCKING from DC-1 nadir) -14870 -6745 -6745 144507010



5-4


Step Name Component Description Mass Mass Stage Station Number [lb] [kg] Total [kg] Total [kg]

4S_AR2 Soyuz 4S (DOCKING at FGB nadir) 14870 6745 6745 151252

011


9P_AR 9P Progress (DOCKING at SM aft) 15287 6934 6934 151041

013

9A_IN1 S1 Truss Segment 16336 7410 015 CETA Cart A 534 242

EATCS Radiator deployed on S1 11232 5095 12747 163788

11A_IN1 P1 Truss Segment 16077 7292 019 CETA Cart B 242

P1 Radiator 5094 12629 176417



023

5S_AR Soyuz 5S (DOCKING at FGB nadir) 14870 6745 6745 183646024

4S_AS2 Soyuz 4S (UNDOCKING from DC1 nadir) -14870 -6745 -6745 176901

025

ULF1_IN1 ISS Core - ULF1_IN1 241122 109371 027 External Stowage Platform 2 (ESP-2) 5871 2663 2872 179773

ULF1_IN2 MPLM (Launch Configuration) berthed to Node 1 19412 8805 8805 188578

028

ULF1_BS MPLM (Return Configuration) back into P/L Bay -19412 -8805 -8805 179773030

10P_AS ISS Core - 10P_AS 238439 108154

032 10 P Progress (UNDOCKING) -15287 -6934 -8151 171622


11P_AS ISS Core - 11P_AS 240090 108903

034 11P Progress (UNDOCKING) -15287 -6934 -6185 172371


12A_IN1 ITS P3/P4 34698 15739 15739 195043



5-5



037

12A_BS Circuit Interupt Device 80 36 36 195080038

6S_AR 6S Soyuz (DOCKING on DC1 nadir) 14870 6745 6745 201825

040

5S_AS 5S Soyuz (UNDOCKING from FGB nadir) -14870 -6745 -6745 195080041

12A.1_IN1 ITS P5 and PVRGF 4371 1983

043 PVRGF 231 105 2087 197167

12A.1_BS ISS Core - 12A.1_BS 239870 108803 044 Pump Module 1188 539

SHOSS Box #1 555 252 MBSU CP 97 44 DDCU CP 118 53 PFCS on ESP 1 -488 -221 567 197734



047

13A_IN1 S3 Truss Segment (attached to P1 port) 4790 2173 049 S3 Rotary Bulkhead (JEMPM) 532 241

S3 Rotary Stator (incl. UTA) 1960 889 S3 Solar Alpha Rotary Joint (JEMEF) 980 445 S3 Upper and Lower ULCS (4) (JEMES) 1311 595 S3 CETA light 24 11 S4 Truss Segment 16042 7277 S4 Beta Gimbals 1839 834 Port Inboard Forward (PIF) PV Solar Array 2368 1074 Port Inboard Aft (PIA) PV Solar Array 2368 1074 S4 IEA Radiator (Stowed) 4791 744 15356 210862

13A.1_IN1 S5 Truss Segment 4085 1853 053 S5 PVRGF 231 105 1958 212820

13A.1_IN2 EAS off-loaded to ICC -1433 -650 -650 212170

054 3S_AS ISS Core - 3S_AS 240220 108962

001 Progress 7P (@ SM Aft) 15288 6934 Soyuz 4S (@ DC1 Nadir) 14871 6745 PMA-2 2565 1164 PMA-3 2575 1168

SM PV Array - Port 1279 580 SM PV Array - Starboard 1279 580

FGB PV Array - Port 551 250



5-6



FGB PV Array - Starboard 551 250 ITS P6 Core 23556 10685



5-7

5.3 ORBITER MASS The primary source for Orbiter mass properties was the SODB. SODB reports from Stage UF-2 (STS-111) through ULF-1 (STS-114) were used. The mission specific events and the respective mass and mass properties were included in each mission. The other sources of data used to determine Orbiter mass properties was the Cargo Element Mass Properties spreadsheets, provided by the Vehicle Integration Performance and Resources (VIPeR) Team. This information is used to modify the SODB reports when there is an update to cargo element mass properties. This information was recorded in the SODB-Derived Orbiter Mass Properties, Table 5.3-1. Generic Orbiter Mass Properties, Table 5.3-2, provides mass properties assessments for Space Shuttle vehicle intervals [After Rendezvous, Intermediate, and Before Separation], which do not have SODB information at the time of data collection for this Data Book. The table was created from the SODB Sequential mass properties for Stage 9A [product number prop02, dated 01/16/02] and Stage 11A [dated 03/04/02] to construct the generic Atlantis and Endeavor orbiters, respectively. Original values are shown in the “SODB Total Orbiter” rows. The deducted payloads are shown in the “Payload Subtract” rows. The resultant mass and mass properties, which are similar to the shuttle without any payload, are shown in the “Generic Orbiter” rows. For 12A.1 and 13A.1 the Atlantis generic Orbiter was used. Due to a lack of data, the generic Atlantis was substituted in place of Space Shuttle Discovery for Stage 13A. For the 12A mission, the Endeavour generic Orbiter was utilized. The mission specific payloads for each shuttle flight were included to develop the Orbiter totals for these missions. NOTE: Products of inertia are positive integrals in Tables 5.3-1 and 5.3-2. Orbiter mass property inputs are reported in the OSRS for these tables. Section 3.0 contains detailed coordinate system descriptions. Refer to Table 6.3-1 for Orbiter to ISS attach points.



5-8




5-9

Table 5.3-1 SODB – Derived Orbiter Mass Properties Units

[English] [Metric]

Mass [lb] [kg]

CMx [in] [m]

CMy [in] [m]

CMz [in] [m]

Ixx [slug*ft2] [kg*m2]

Iyy [slug*ft2] [kg*m2]

Izz [slug*ft2] [kg*m2]

Ixy [slug*ft2] [kg*m2]

Ixz [slug*ft2] [kg*m2]

Iyz [slug*ft2] [kg*m2]

STEP 004 Stage UF2_AR, Prop 02, 4/9/2002, ISS Dock (DY:001 HR:018 MN:031 SC:000), adjusted due to updated cargo mass properties Orbiter in SSACS [Metric] 110264.0 10.842 -0.006 16.791 10829834 10413470 1308633 -511 -359654 13932 Orbiter in OSRS [Metric] 110264.0 27.715 -0.007 9.546 1308633 10413470 10829834 13932 359654 511Orbiter in OSRS [English] 243090.4 1091.2 -0.3 375.8 965198 7680581 7987675 10276 265267 377 STEP 005, Stage UF2_INT1, Prop 02, 4/9/2002, MPLM UF2 DEPLOYABLE (DY:002 HR:005 MN:000 SC:000), adjusted due to differences in equipment transfers Orbiter in SSACS [Metric] 99779.8 10.901 -0.018 16.757 10780168 10359720 1274880 222 -355568 13069 Orbiter in OSRS [Metric] 99779.8 27.682 -0.019 9.487 1274880 10359720 10780168 13069 355568 -222Orbiter in OSRS [English] 219976.9 1089.8 -0.8 373.5 940303 7640937 7951044 9639 262254 -164 STEP 006, Stage UF2_INT2, Prop 02, 4/9/2002, SMDP DEPLOYABLE(DY:002 HR:006 MN:000 SC:000), adjusted due to differences in equipment transfers Orbiter in SSACS [Metric] 99665.7 10.901 -0.019 16.754 10777735 10357592 1274316 264 -355190 12948 Orbiter in OSRS [Metric] 99665.7 27.679 -0.019 9.487 1274316 10357592 10777735 12948 355190 -264Orbiter in OSRS [English] 219725.3 1089.7 -0.8 373.5 939887 7639367 7949249 9550 261975 -195 STEP 007, Stage UF2_INT3, Prop 02, 4/9/2002, MPLM UF2 RETRIEVEABLE (DY:008 HR:003 MN:000 SC:000), adjusted due to differences in equipment transfers Orbiter in SSACS [Metric] 98130.5 10.914 -0.016 16.872 10685103 10263781 1269912 253 -365672 12326 Orbiter in OSRS [Metric] 98130.5 27.796 -0.017 9.474 1269912 10263781 10685103 12326 365672 -253Orbiter in OSRS [English] 216340.7 1094.3 -0.7 373.0 936639 7570176 7880927 9091 269706 -186 STEP 008, STAGE UF2_BS, Prop 02, 4/9/2002, FINAL SEP (DY:009 HR:017 MN:000 SC:000), adjusted due to differences in the MPLM down mass Orbiter in SSACS [Metric] 106541.2 10.856 -0.000 16.933 10501404 10084340 1287145 -43 -345958 14183



5-10


[English] [Metric]

Mass [lb] [kg]

CMx [in] [m]

CMy [in] [m]

CMz [in] [m]







Orbiter in OSRS [Metric] 106541.2 27.857 -0.001 9.532 1287145 10084340 10501404 14183 345958 43Orbiter in OSRS [English] 234883.1 1096.7 -0.0 375.3 949350 7437827 7745438 10461 255165 32 STEP 014, Stage 9A_AR, Prop 02 1/29/02, ISS DOCK (DY:001 HR:019 MN:058 SC:000) Orbiter in SSACS [Metric] 110293.7 10.858 -0.006 16.715 10859440 10470318 1297676 -639 -296435 7534 Orbiter in OSRS [Metric] 110293.7 27.639 -0.007 9.530 1297676 10470318 10859440 7534 296435 639Orbiter in OSRS [English] 243155.9 1088.2 -0.3 375.2 957116 7722510 8009512 5557 218639 471 STEP 015, Stage 9A_IN1, Prop 02, 1/29/02, DEPLOY SEGMENT S1(DY:002 HR:014 MN:000 SC:000), adjusted to account for differences in equipment transfer Orbiter in SSACS [Metric] 97541.0 10.975 -0.016 16.984 10617307 10216874 1258835 1359 -335237 11391 Orbiter in OSRS [Metric] 97541.0 27.908 -0.017 9.413 1258835 10216874 10617307 11391 335237 -1359Orbiter in OSRS [English] 215041.0 1098.7 -0.7 370.6 928469 7535580 7830924 8402 247258 -1002 STEP 017, Stage 9A_BS, Prop 02, 1/29/02, ISS Undock (DY:007 HR:016 MN:058 SC:000) Orbiter in SSACS [Metric] 96741.2 10.964 -0.011 17.004 10591643 10191954 1253202 2197 -332712 9594 Orbiter in OSRS [Metric] 96741.2 27.929 -0.011 9.424 1253202 10191954 10591643 9594 332712 -2197Orbiter in OSRS [English] 213277.9 1099.6 -0.4 371.0 924315 7517199 7811995 7076 245396 -1620 STEP 018, 11A_AR, Prop 02, 3/04/02, ORBITER POST RNDZ, adjusted due to updated cargo element mass properties Orbiter in SSACS [Metric] 110426.8 10.840 -0.009 16.705 11026811 10534337 1398586 31209 -291171 49747 Orbiter in OSRS [Metric] 110426.8 27.630 -0.010 9.548 1398586 10534337 11026811 49747 291171 -31209Orbiter in OSRS [English] 243449.4 1087.8 -0.4 375.9 1031544 7769728 8132958 36692 214757 -23018 STEP 019, 11A_IN1, Prop 02, 3/04/02, SEGMENT P1 Orbiter in SSACS [Metric] 97797.8 10.956 -0.016 16.972 10734041 10237337 1358116 32781 -320717 52257 Orbiter in OSRS [Metric] 97797.8 27.897 -0.016 9.432 1358116 10237337 10734041 52257 320717 -32781Orbiter in OSRS [English] 215607.2 1098.3 -0.6 371.4 1001695 7550672 7917022 38543 236549 -24178



5-11


[English] [Metric]

Mass [lb] [kg]

CMx [in] [m]

CMy [in] [m]

CMz [in] [m]







STEP 020, 11A_BS, Prop 02, 3/04/02, ISS UNDOCKING Orbiter in SSACS [Metric] 97137.9 10.944 -0.011 16.988 10729252 10233253 1353616 33507 -318347 51615 Orbiter in OSRS [Metric] 97137.9 27.913 -0.012 9.444 1353616 10233253 10729252 51615 318347 -33507Orbiter in OSRS [English] 214152.4 1098.9 -0.5 371.8 998376 7547660 7913490 38070 234800 -24713 STEP 026, Stage ULF1_AR, Prop 37, 2/15/02, E-17 ORBITER POST OMS 7 BURN, adjusted for updated cargo element mass properties numbers Orbiter in SSACS [Metric] 110580.9 10.886 -0.005 16.746 10706327 10304752 1291652 696 -350739 7997 Orbiter in OSRS [Metric] 110580.9 27.670 -0.005 9.502 1291652 10304752 10706327 7997 350739 -696Orbiter in OSRS [English] 243789.2 1089.4 -0.2 374.1 952674 7600395 7896581 5898 258692 -514 STEP 027, Stage ULF1_IN1, Prop 37, 2/15/02, E-17 ORBITER POST OMS 7 BURN, adjusted due to updated cargo element mass properties numbers and transfers Orbiter in SSACS [Metric] 107502.0 10.915 -0.004 16.862 10624822 10220464 1286437 732 -361170 8217 Orbiter in OSRS [Metric] 107502.0 27.787 -0.005 9.473 1286437 10220464 10624822 8217 361170 -732Orbiter in OSRS [English] 237001.3 1094.0 -0.2 372.9 948827 7538227 7836466 6060 266385 -540 STEP 028, Stage ULF1_IN2, Prop 37, 2/15/02, E-17 ORBITER POST OMS 7 BURN, adjusted due to updated cargo element mass properties numbers and transfers Orbiter in SSACS [Metric] 98612.6 10.979 -0.012 16.847 10584109 10179162 1254384 1401 -358806 9011 Orbiter in OSRS [Metric] 98612.6 27.771 -0.013 9.409 1254384 10179162 10584109 9011 358806 -1401Orbiter in OSRS [English] 217403.6 1093.4 -0.5 370.4 925186 7507764 7806438 6646 264642 -1034 STEP 030, ULF1_BS. Prop 37, 2/15/02, E-29 ORBITER PAYLOAD DOORS CLOSED, adjusted due to updated cargo element mass properties Orbiter in SSACS [Metric] 105955.4 10.827 -0.005 16.889 10527161 10185918 1250773 594 -323204 9724 Orbiter in OSRS [Metric] 105955.4 27.814 -0.006 9.561 1250773 10185918 10527161 9724 323204 -594Orbiter in OSRS [English] 233591.6 1095.0 -0.2 376.4 922523 7512747 7764435 7172 238383 -438



5-12

This page included for formatting purposes



5-13

Table 5.3-2 Generic Orbiter Mass Properties Units

[English] [Metric]

Mass [lb] [kg]

CMx [in] [m]

CMy [in] [m]

CMz [in] [m]







***** Generic Orbiter for Atlantis Flights; based off Stage 9A Orbiter – Used for Flights 12A.1 and 13A.1 Atlantis Orbiter After Rendezvous - STS-112 (9A) Prop 02 report 01/16/02 -- Deploy Segment S1, modified to account for differences in cargo transfers Orbiter OSRS [English] 215041.0 1098.75 -0.67 370.60 1706754 13852243 14395158 15444 454521 -1842 Payload Subtract [English] 0.0 0.00 0.00 0.00 0 0 0 0 0 0 Generic Orbiter OSRS [English] 215041.0 1098.75 -0.67 370.60 1706754 13852243 14395158 15444 454521 -1842 Generic Orbiter OSRS [Metric] 97541.0 27.908 -0.017 9.413 1258835 10216874 10617307 11391 335237 -1359 Generic Orbiter SSACS [Metric] 97541.0 10.975 -0.016 16.984 10617307 10216874 1258835 1359 -335237 11391 Atlantis Orbiter After Intermediate - STS-112 (9A) Prop 02 report 01/16/02 -- Deploy Segment S1, modified to account for differences in cargo transfers Orbiter OSRS [English] 215041.0 1098.75 -0.67 370.60 1706754 13852243 14395158 15444 454521 -1842 Payload Subtract [English] 0.0 0.00 0.00 0.00 0 0 0 0 0 0 Generic Orbiter OSRS [English] 215041.0 1098.75 -0.67 370.60 1706754 13852243 14395158 15444 454521 -1842 Generic Orbiter OSRS [Metric] 97541.0 27.908 -0.017 9.413 1258835 10216874 10617307 11391 335237 -1359 Generic Orbiter SSACS [Metric] 97541.0 10.975 -0.016 16.984 10617307 10216874 1258835 1359 -335237 11391 Atlantis Orbiter Before Separation - STS-112 (9A) Prop 02 report 01/16/02 -- Orbiter - ISS Undock Orbiter OSRS [English] 213277.9 1099.60 -0.50 371.00 924315 7517200 7811995 7076 245396 -1620 Payload Subtract [English] 0.0 0.00 0.00 0.00 0 0 0 0 0 0 Generic Orbiter OSRS [English] 213277.9 1099.60 -0.50 371.00 924315 7517200 7811995 7076 245396 -1620 Generic Orbiter OSRS [Metric] 96741.2 27.929 -0.011 9.424 1253202 10191954 10591643 9594 332712 -2197 Generic Orbiter SSACS [Metric] 96741.2 10.964 -0.011 17.004 10591643 10191954 1253202 2197 -332712 9594



5-14

Table 5.3-2 Generic Orbiter Mass Properties Units

[English] [Metric]

Mass [lb] [kg]

CMx [in] [m]

CMy [in] [m]

CMz [in] [m]







***** Generic Orbiter for Endeavour Flights; Based off Stage 11A Orbiter – Used for Stages 12A and 13A Endeavour Orbiter After Rendezvous - STS-113 (11A) Prop 02, 3/04/02, ORBITER POST RNDZ Orbiter OSRS [English] 243171.6 1085.90 -0.49 375.27 952020 7810234 8112030 5208 224358 1234 Payload Subtract [English] -28051.9 1006.30 1.43 410.24 -22243 -166063 -171057 797 2422 -812 Generic Orbiter OSRS [English] 215119.7 1096.28 -0.74 370.71 921389 7592477 7897616 7048 245816 -37 Generic Orbiter OSRS [Metric] 97576.7 27.846 -0.019 9.416 1249236 10294016 10707730 9556 333282 -50 Generic Orbiter SSACS [Metric] 110426.8 10.840 -0.009 16.705 11026811 10534337 1398586 31209 -291171 49747 Endeavour Orbiter Intermediate - STS-113 (11A) Prop 02, 3/04/02, SEGMENT P1 Orbiter OSRS [English] 215607.2 1098.30 -0.64 371.35 1001695 7550672 7917022 38543 236549 -24178 Payload Subtract [English] 0.0 0.00 0.00 0.00 0 0 0 0 0 0 Generic Orbiter OSRS [English] 215607.2 1098.30 -0.64 371.35 1001695 7550672 7917022 38543 236549 -24178 Generic Orbiter OSRS [Metric] 97797.8 27.897 -0.016 9.432 1358116 10237337 10734041 52257 320717 -32781 Generic Orbiter SSACS [Metric] 97797.8 10.956 -0.016 16.972 10734041 10237337 1358116 32781 -320717 52257 Endeavour Orbiter Before Separation - STS-113 (11A) Prop 02, 3/04/02, ISS UNDOCKING Orbiter OSRS [English] 214152.4 1098.94 -0.47 371.80 998376 7547660 7913490 38070 234800 -24713 Payload Subtract [English] 0 0.00 0.00 0.00 0 0 0 0 0 0 Generic Orbiter OSRS [English] 214152.4 1098.94 -0.47 371.80 998376 7547660 7913490 38070 234800 -24713 Generic Orbiter OSRS [Metric] 97137.9 27.913 -0.012 9.444 1353616 10233253 10729252 51615 318347 -33507 Generic Orbiter SSACS [Metric] 97137.9 10.944 -0.011 16.988 10729252 10233253 1353616 33507 -318347 51615



5-15

5.4 MASSES OF ORBITER ATTACHED CONFIGURATIONS

The Orbiter payload, or cargo mass properties were included in the SODB total Orbiter mass, and can be found in Tables 5.3-1 or 5.3-2. The ISS total mass can be found in Table 5.2-1. The Orbiter total mass, and ISS total mass can also be found in Section 7, in the mass and aerodynamic properties data sets. An explanation of these data sets can be found in Section 7.8, titled Illustrations and Configuration Mass Properties.

5.5 MASS PROPERTIES OF CORE COMPONENTS

For missions up to and including 2A.2B, VIPeR, Resources and Integration (RAI), and RSC-E concurred on the ISS On-Orbit Mass Properties. Following the application of a new data exchange protocol, the baseline data was further updated via a series of additions and deductions over subsequent analyses performed on various configurations associated with all flights up to 7A.1. As a result, and since Flight 2A.2B, the mass properties of specific elements, such as the Zarya FGB and the Zvezda Service Module, have been maintained separately by VIPeR and RSC-E. Without formal concurrence on the sole account of payload transfers to and from those elements, RSC-E has been providing both VIPeR and Lockheed Martin RAI teams with mass properties for progress and Soyuz flights, as well as for the Pirs Docking Compartment. Users of the mass properties and aerodynamic data specified in this Data Book, will notice that a significant portion of a configuration’s mass is lumped in with an ISS Core Station component. In general, this component consists of all elements of the ISS that do not move, change orientation, or undergo deployment or stowage. This approach can be seen in Table 5.2-1 and in the core station element properties tables throughout this Data Book.



5-16




6-1

6.0 GEOMETRY DATA INTEGRATION

The ISS and integrated Space Shuttle geometry inputs were collected, modeled, and organized to correspond with mass and assembly inputs. The Configuration List, Table 4.0-1, was used as a reference to build all mass properties and geometric models. After mass and assembly inputs were integrated into SEMDA Lab mass spreadsheets, information from these spreadsheets were applied to develop and update geometry model components and assemblies.

6.1 ISS GEOMETRY

The geometric representation for ISS components making up the assembly flight configurations is approximate. NASA modules were based on electronic files received from the Boeing-PIT. The CSA electronic geometry files, transferred through Boeing, were used to model Canadian robotics equipment. Russian geometry baselines and updates were obtained from Russian engineers via the TIM and regular teleconferences. Russian engineers provided Zarya FGB, Service Module, and Pirs DC 1 data books, drawings and electronic files. See entries in the 2.1 Applicable Documents section for further details.

Information in this document was based on solid geometry models constructed with the SDRC I-DEAS Master Series modeling package. Configuration models were defined using the data associated with the Table 4.0-1 Configuration List. ISS geometry was modeled in the SSACS.

6.2 ORBITER GEOMETRY

The geometric representation of the Space Shuttle and associated integrated payload components is approximate. Space Shuttle geometry was created from dimensioned drawings and a computer model produced by Boeing for production of the Endeavour Orbiter Vehicle (OV) 105. Additional information sources include the National Space Transportation System (NSTS) SODB and amendments, and NSTS documents defining the ODS, Androgynous Peripheral Assembly System (APAS), and ISS PMA mating interfaces. Figure 3.3-1 and Section 3.3 provide basic Orbiter dimensions and descriptions of the various positions of the ODS. The outer surfaces of the Space Shuttle body, wings, and vertical tail were based on a detailed finite element model. The resulting model geometry was verified with a three-dimensional electronic wire frame geometry model from Boeing-North American, at Huntington Beach, California. Orbiter base mass properties were assigned to the model as described in Section 5.3. Data inputs were based on the OSRS, as defined in Section 3.3.

On-orbit analysis data outputs in this document, including those related to Orbiter vehicles, are reported in the SSACS frame as described in Section 3.2. On-orbit output data sets are derived from solid geometry models constructed using I-DEAS Master Series software package.



6-2

6.3 ORBITER TO ISS ATTACH POINTS

The Table 6.3-1 lists the Orbiter to ISS docking reference point positions in the SSACS. This table also supplies the orientation of the Orbiter, the ISS docking module to which the Orbiter was docked, and the direction of the Orbiter tail.

Table 6.3-1 Orbiter to ISS Attach Points STAGE ATTACH POINTS PMA 2 PMA 3

x y z x y z

mm 8698 -1 5560 -4463 -4379 5558

UF2-13A.1

Orbiter docks to PMA 2 attached to Destiny Lab forward CBM [clocked for Orbiter tail nadir docking.]

PMA 3 is located at Unity Node 1 port docking port [clocked for Orbiter tail nadir docking].

in 342.4 0.0 218.9 -175.7 -172.4 218.8



7-1

7.0 CONFIGURATION DATA Section 7 provides illustrations and descriptions of ISS configuration changes including Orbiter, Progress and Soyuz arrivals or departure, module movements, truss structure movements, and solar array or radiator retractions or deployments. [Additional illustrations and descriptions exist for mated ISS-Orbiter operations.] Table 4.0-1 provides a list of each configuration included in this document. Configurations come in two categories: Free Flying Configurations and Orbiter Attached Configurations. Section 7.0 details types of data sets supplied for each configuration. This section of the Data Book contains 58 Steps that describe the assembly sequence of the ISS from 3S after separation to 13A.1 after orbiter separation. Those configurations from Stages 10A to 16A [Assembly Complete] were omitted because these configurations fall outside the 18-month analysis window for this Data Book. The following paragraphs describe features of each Configuration section. Configuration sections consist of these data categories:

�� Section Title

�� Configuration Description

�� Orbiter Attach Point Location

�� Element Interfaces

�� Element Properties

7.1 SECTION TITLE The Section Title lists a configuration number on the first line, a step number on the second line, a stage or flight description on the third line. The fourth line contains data including a mission flight identification number assigned by NASA or RSA with a vehicle name. The configuration number is a specific number for each flight, which was agreed upon by NASA and RSC-E during the November 06, 2001 Assembly and Configuration Video conference. The step number is the sequential order of events specifically for the current assembly sequence Data Book. Table 4.0-1 provides a list of each configuration. Section 4.0 provides information on nomenclature used in the stage and flight designations. 7.2 CONFIGURATION DESCRIPTION The information provided in bullet format at the beginning of each configuration summaries the activities that occur. This information is derived from the Assembly Matrix, Assembly Sequence, and Assembly Overviews. Major configuration events can include docking and undocking, relocation of modules or other structures, EVAs, rack transfers, deployments and retractions, and ISS flight modes. This section includes descriptions of assumptions made in creation of geometry, mass properties, or assemblies representing ISS assembly operations.



7-2

As described in Section 3.2, the ISS flight mode is defined by the orientation of the SSACS frame Y-axis truss segment with respect to coordinates of the orbital LVLH coordinate system. Alignment of the SSACS Y-axis normal to the orbital plane [YA in the LVLH] defines the LVLH flight mode. When corrections for torque equilibrium attitude are insignificant, the Z-axis should point to the nadir and the X along the velocity vector.

7.3 ELEMENT INTERFACES The Element Interfaces table indicates the location of each docking or berthing mechanism for all elements with this hardware after delivery to the ISS, or after repositioning once on orbit. Locations are given in millimeters in the SSACS frame. These table values are updated whenever an element with docking or berthing mechanisms changes orientation or location.

7.4 ORBITER ATTACH POINT LOCATION An Orbiter to ISS Attach Point Location Table provides the attached locations in inches and millimeters. This table includes the orientation of an Orbiter when docked. This information is available for all configurations on Table 6.3-1. A reference to this table appears only in After Rendezvous, Orbiter attached configuration sections.

7.5 ELEMENT PROPERTIES The mass, center of mass, reference point, and inertia tensor are provided for every new major element which first arrives on orbit or any major element which is moved within the range shown in Section 1, Introduction, of this data book. When the element first arrives on orbit or undergoes a major geometry change a four-view illustration is shown. Note that the element illustrated may be rotated for clarity or for compatibility with the SSP-30219 Coordinate System document. The illustration provides overall dimensions of the element or group of elements in millimeters and inches. A reference point location is given in millimeters to both the SSACS and RSA Analysis Coordinate Systems. The mass properties are given when the element either (a) increases or decreases in mass, (b) moves to a new location on the ISS, or (c) changes configuration [such as mechanism deployment or retraction].

7.6 ILLUSTRATIONS AND CONFIGURATION MASS PROPERTIES Each configuration is shown in an isometric illustration. The reverse side of this page shows a mass and aerodynamic properties for the configuration. For mated ISS-Orbiter configurations, the mass and aerodynamic properties are provided for the mated stack on the reverse of the configuration illustration. Additional data sets are provided for the Orbiter and ISS properties. The Orbiter and ISS properties pages are described further in the following sections. These data sets include mass, center of mass, inertia tensor, principal moments of inertia, centers of pressure, and projected areas. Titles on these pages show the configuration number and a stage or flight description. Section 4.0 provides information on typical nomenclature used in the stage and flight designations.



7-3

The mass and aerodynamic properties data sets in this section contain these items:

Total Mass [lb.] Mass of configurations in pounds Total Mass [kg] Mass of configuration in kilograms Center of Mass: X Distance along X-axis from origin in SSACS in feet and meters Y Distance along Y-axis from origin in SSACS in feet and meters Z Distance along Z-axis from origin in SSACS in feet and meters Inertia Tensor: Ixx, Iyy, Izz Moments of inertia with respect to SSACS frame axes in slug-ft2

and kg-m2 about the center of mass Ixy, Iyz, Ixz Products of inertia [negative integrals] with respect to SSACS

frame axes in slug-ft2 and kg-m2 about the center of mass Principal Moments Of Inertia:

Ixx, Iyy, Izz Principal moments of inertia with respect to SSACS frame axes in slug-ft2 and kg-m2 about the center of mass

Principal to Body Euler Angles:

Roll, Pitch, Yaw Angles required for rotating principal axes to body axes. CP [Centers of Pressure]:

CPX Distance in YZ plane from ISS center of mass in feet and meters. CPY Distance in XZ plane from ISS center of mass in feet and meters. CPZ Distance in XY plane from ISS center of mass in feet and meters. Projected Area:

X-Axis Configuration projected area in the YZ plane, in ft2 and m2

Y-Axis Configuration projected area in the XZ plane, in ft2 and m2

Z-Axis Configuration projected area in the XY plane, in ft2 and m2



7-4

7.7 MASS PROPERTIES FOR ORBITER AT BEGINNING, DURING, AND END OF MATED OPERATIONS

Mass and aerodynamic properties data sets are provided in the Orbiter attached configuration sections. These data sets fall into three categories: The first category of Orbiter attached data sets is entitled, “XX Orbiter – After Rendezvous,” the second is entitled, “XX Orbiter – Intermediate X,” and the third type is entitled, “XX Orbiter – Before Separation.” The “XX” represents the space agency launch designation, such as Stage 8A, for the configuration number shown in the preceding line. The Orbiter properties shown for the beginning, or After Rendezvous operation, are calculated immediately after the Orbiter docks and before payloads are moved to the ISS. The Orbiter properties shown for the Intermediate operations are calculated after selected payloads have moved to the ISS, but before completion of Orbiter based assembly operations. Orbiter properties shown for the end, or Before Separation operation, are calculated after payload transfer, Orbiter-based EVAs, and immediately before Orbiter undock from the ISS. Orbiter mass is shown in Table 5.3-1 or Table 5.3-2.

7.8 AERODYNAMICS Aerodynamic models for multi-body vehicles with articulating elements are based on reference areas and drag coefficients with provisions for shadowing effects and changing positions to the direction of flight and atmospheric flow. This Data Book provides projected areas and centers of pressure allowing for shadowing. Drag coefficients are not provided. Area properties are computed by MODGEN by two different procedures. Of the two procedures, the primary and most accurate method, represents each flight or assembly stage as an assembly of components. Each component is modeled in turn as an assembly of polygons approximating a more detailed geometry. Polygons are mapped onto a 101 X 101 expandable grid of rectangular cells for each axis in an orthogonal reference coordinate system. Projected areas are determined by multiplying the total number of shadowed cells by the cell areas. For partially shadowed cells of the grid, if the center of the cell is shadowed, the cell is considered fully covered. CP is determined by the averaged cell location for each axis. CP vectors are transformed from the analysis coordinate system to the vehicle or body center of mass as shown in the tables of Sections 7.9 [Volume I] and 8.0 [Volume II] of the text. These data sets are available in a File Transfer Protocol (ftp) account as the “*.acp” family of files in the electronic access directories. The secondary computation method for calculation of aerodynamic properties is based on modeling each component of the vehicle as a circular plate. For each reference axis, the cumulative effect of each geometric component is represented as a circular plate of corresponding projected area and moment arm for center of pressure. Results for model bodies and assembly configurations are available via electronic access in the “*.smry” family of files. In both methods, one coordinate of each center of pressure vector is undefined.



7-5

For example, in the CPx vector, the two methods described determine values for the Y and Z coordinates but not for X. This undefined coordinate is set to zero, that is, to the center of mass along the x-axis. 7.9 CONFIGURATION DATA SECTIONS This portion of the document contains 64 configuration sections describing the ISS assembly sequence from Flight 6P After Rendezvous to Stage 13A After Separation.



7-6

CONFIGURATION 053

Stage 7A - After Separation

ISS PHASE 2 COMPLETED



7-7

CONFIGURATION 086

STEP 001

Flight 3S - After Separation

(RSA Flight ID: 207)

�� Prior to Flight 3S_AS:

o Flight 1A/R delivered Zarya Control Module FGB in November 1998.

o Flight 2A [STS-88] delivered Unity Node 1, PMA 1 and PMA 2 to mate with

Zarya FGB Module in December 1998.

o Stage 2A.1 [STS-96] delivered the first outfitting with Strela Operation

Station and EVA Node bags that were placed on PMA 1 in May 1999 and

Node 1 in June 1999.

o Stage 2A.2A [STS-101] delivered second outfitting for Node 1 and Zarya

FGB in May 2000. o Stage 1R [Russian] delivered Zvezda Service Module that docked to FGB

in July 2000. Service Module provided early living quarters to ISS.

o Flight 1P [Progress M1-3] docked to Zvezda Service Module aft docking

port. Progress supplied propellant and consumables to ISS in August 2000.

o Stage 2A.2B [STS-106] delivered a third set of logistics for the ISS in

September 2000.

o Stage 3A [STS-92] delivered Zenith 1 (Z1) Integrated Truss Assembly

(ITA), PMA 3, Ku-band Antenna, and S-band Antenna in October 2000.

o 1P [Progress M1-3] undocked from Zvezda Service Module aft docking

port in October 2000.

o Flight 2R [Soyuz 1S TM-31] docked to Zvezda Service Module aft docking

port to deliver first ISS three-man crew in November 2000.

o Flight 2P [Progress M1] docked to Zarya FGB nadir docking port with

supplies to outfit the ISS in November 2000.

o Flight 2P [Progress M1] separated from Zarya FGB nadir docking port after

dry cargo, waste loading, and propellant transfer in December 2000.



7-8

CONFIGURATION 086

STEP 001



o Stage 4A [STS-97] delivered ITS P6 to ISS. P6 solar arrays, forward and

aft radiators, EVA Bag, and Plasma Probe deployed in December 2000.

o Flight 2P [Progress M1] docked to Zvezda Service Module aft docking port

in December 2000.

o Flight 2P [Progress M1] undocked from Zvezda Service Module aft docking

port in February 2001.

o Stage 5A [STS-98] delivered Destiny Laboratory Module to ISS. P6

starboard radiator deployed. Lab power, PDGF, and window shutter

gearbox installed in February 2001.

o Flight 2R [Soyuz 1S TM-31] undocked from Zvezda Service Module aft

docking port and redocked to Zarya FGB nadir docking port in February

2001.

o Flight 3P [Progress M-44] docked to Zvezda Service Module aft docking

port in February 2001.

o Stage 5A.1 [STS-102] installed Leonardo MPLM and LCA. Second ISS

crew arrived; first crew returned to Earth in March 2001.

o Flight 3P [Progress M-44] undocked from Zvezda Service Module aft

docking port after unloading propellant and dry cargo and loading waste in

April 2001.

o Flight 2R [Soyuz 1S TM-31] undocked from Zarya FGB nadir docking port

and docked to Zvezda Service Module aft docking port in April 2001.

o Stage 6A [STS-100] delivered SLP, UHF Antenna, the Space Station RMS

Lab PDGF, and Raffaello MPLM to ISS in April 2001.

o Flight 2S [Soyuz TM-32] docked to Zarya FGB nadir docking port in April

2001.



7-9

CONFIGURATION 086

STEP 001



o Flight 2R [Soyuz 1S TM-31] undocked for the third time from Zvezda

Service Module aft docking port in May 2001


port in May 2001.

o Stage 7A [STS-104] delivered the Airlock module and four HPGA units in

July 2001.

o Stage 7A.1 [STS-105] installed Donatello MPLM and delivered EAS,

APFR, and (2) MISSEs. Third ISS crew arrived. Second ISS crew returned

to Earth in August 2001.

o Flight 4P [Progress M1-6] undocked from Zvezda Service Module aft

docking port after unloading propellant, dry cargo, and loading waste in

August 2001.

o Flight 5P [Progress M-45] docked to Zvezda Service Module aft docking

port and delivers the Russian experiment MPAC/SEEDs in August 2001.

o Stage 4R [Pirs DC 1] delivered the Pirs DC 1 and the second Strela Cargo

Boom in September 2001. USI detached from Pirs DC 1. Soyuz docking

target deployed on Pirs DC 1 nadir. MPAC/SEEDs deployed on Service

Module.

o Flight 2S [Soyuz TM-32] undocked from Zarya FGB nadir docking port and

docked to Pirs DC 1 nadir docking port in October 2001. EVA egress

ladder and boom with antenna deployed on Pirs DC 1.

o Flight 3S [Soyuz TM-33] docked to Zarya FGB nadir docking port in

October 2001.

o Flight 2S[Soyuz TM-32] undocked from Pirs DC 1 nadir docking port in

October 2001.



7-10

CONFIGURATION 086

STEP 001



o Flight 5P [Progress M-45] undocked from Zvezda Service Module aft

docking port after unloading propellant, dry cargo, and loading waste in

November 2001.


port in November 2001.

o Stage UF 1 [STS-108] installed Raffaello MPLM to outfit ISS in December

2001.

o Flight 6P [Progress M1-7] undocked from Zvezda Service Module aft

docking port after unloading propellant, dry cargo and loading waste in

March 2002. Prior to 6P, Strela 1 is relocated from PMA 1 to Pirs DC 1.


port in March 2002.

o Stage 8A [STS-110] delivered ITS S0 truss, airlock spur, CETA lights, Lab

umbilicals, PWP and MT in April 2002.

o Flight 4S [Soyuz TM-34] docked to Pirs DC 1 nadir docking port in

September 2001.



7-11

CONFIGURATION 086

STEP 001


(RSA Flight ID: 207) Element Interfaces: Description No. Location [SSACS] Mode X [mm] Y [mm] Z [mm] PMA 3 on Unity Node 1 [nadir] CBM [zenith] 1 -4463 -1 6844 Passive APAS [nadir] 1 -3752 -1 9231 Passive ITS Z1 CBM [nadir] 1 -4462 5 2855 Passive CBM [forward] 2 -3268 5 474 Active Zvezda Service Module Hybrid [forward] 1 -22577 4 4139 Passive [cone] Probe and Cone [aft] 2 -35689 4 4139 Passive [cone] Hybrid [zenith] 3 -23701 4 3015 Passive [cone] Hybrid [nadir] 4 -23701 4 5263 Passive [cone]PMA 2 [Destiny Lab forward] APAS [forward] 1 8698 -1 5560 Passive CBM [aft, includes seal] 1 6314 0 4850 Passive Unity Node 1 CBM [forward] 1 -2435 0 4850 Active CBM [aft] 2 -7628 4 4850 Active CBM [zenith] 3 -4462 5 2855 Active CBM [starboard] 4 -4463 1997 4851 Active CBM [nadir] 5 -4463 -1 6844 Active CBM [port] 6 -4463 -1992 4847 Active PMA 1 on Unity [aft CBM] CBM [forward] 1 -7628 4 4850 Passive APAS [aft] 1 -10016 4 4139 Active Zarya FGB APAS [forward] 1 -10016 4 4139 Passive Hybrid [aft] 2 -22577 4 4139 Active [probe] Probe and Cone [nadir] 3 -11138 4 5279 Passive [cone]Destiny Lab Module [Unity forward]

CBM [forward] 1 6314 0 4850 Active CBM [aft] 2 -2435 0 4850 Passive US Airlock [on Unity Node 1 starboard]

EVA Hatch 1 -4471 6655 5882 - CBM [port] 1 -4463 1997 4851 Passive Pirs DC 1 [on Zvezda nadir] Hybrid [zenith] 1 -23701 4 5263 Probe Probe and Cone [nadir] 1 -23701 4 9312 Cone



7-12

CONFIGURATION 086

STEP 001



�� Flight 3S [Soyuz TM-33] vehicle undocked from Zarya FGB nadir docking port

after 4S Soyuz vehicle arrival to Pirs DC – nadir.

�� 4S remains docked to the Pirs DC 1 nadir docking port maintaining crew return

capability previously assured by 3S Soyuz vehicle.

Element Properties: ISS Core Assembly - 3S_AS Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -10550 X = N/A N/A 796087 -189539 445473108962 Y = 280 Y = N/A N/A -189539 16580551 -63067

Z = 3720 Z = N/A N/A 445473 -63067 16544560Reference Point Description: None



7-13

CONFIGURATION 086 STEP 001



Element Properties: Zarya FGB Assembly Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = -10016 -25323 N/A N/A N/AN/A Y = N/A Y = 4 0 N/A N/A N/A

Z = N/A Z = 4139 0 N/A N/A N/AReference Point Description: Center of forward APAS interface plane



7-14




Element Properties: Unity Node 1 with PMA 1 AssemblyMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = -2435 -32904 N/A N/A N/AN/A Y = N/A Y = 0 -711 N/A N/A N/A

Z = N/A Z = 4850 4 N/A N/A N/AReference Point Description: Center of forward CBM interface plane



7-15




Element Properties: APFR (on PMA 1 02-04 WIF)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = -9297 -26042 N/A N/A N/AN/A Y = N/A Y = -283 843 N/A N/A N/A

Z = N/A Z = 3296 287 N/A N/A N/AReference Point Description: Center of interface plane with WIF



7-16




Element Properties: OTD (on PMA 1 02-05 WIF)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = -9297 -26042 N/A N/A N/AN/A Y = N/A Y = -664 596 N/A N/A N/A

Z = N/A Z = 3543 668 N/A N/A N/AReference Point Description: Center of interface plane with Worksite Interface (WIF)



7-17




Element Properties: Portable Foot Restraint and Workstation Stanchion (PFRWS) (on PMA 1 01-02 WIF)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]


Z = N/A Z = 3392 -1150 N/A N/A N/AReference Point Description: Center of interface plane with APFR socket



7-18




Element Properties: Zvezda Service Module AssemblyMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]


Z = N/A Z = 4139 0 N/A N/A N/AReference Point Description: Center of forward docking interface plane



7-19




Element Properties: Z1 Assembly (deployed Ku-Band antenna and umbilical tray; keel moved)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]


Z = N/A Z = 474 -1 N/A N/A N/AReference Point Description: Center of forward CBM interface plane



7-20




Element Properties: Interoperable APFR (on Z1 02-01 WIF)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]


Z = N/A Z = 2070 -1824 N/A N/A N/AReference Point Description: Center of interface plane with WIF



7-21




Element Properties: P6 Assembly (with forward, aft, and starboard EATCS radiators deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4420 X = -4532 -30807 204630 -288 899914546 Y = 283 Y = -2497 7489 -288 240084 -16802

Z = -8468 Z = -3350 2501 8999 -16802 107011Reference Point Description: Center of the end of nadir keel pin



7-22




Element Properties: P6 POA Solar Array, deployed (on P6 port)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -5177 X = -5200 -30139 176381 -41 01062 Y = -14435 Y = -1450 18019 -41 8317 91

Z = -13652 Z = -13880 1454 0 91 184491Reference Point Description: Center of PV mast canister interface with beta gimbal



7-23




Element Properties: S-band Antenna on P6Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -2652 X = -2697 -32642 15 1 2103 Y = 471 Y = 821 16355 1 16 -4

Z = -13471 Z = -12216 -817 2 -4 7Reference Point Description: Center of interface plane



7-24

CONFIGURATION 086

STEP 001



Element Properties: Plasma Probe (on P6)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -3576 X = -3624 -31715 2 0 -139 Y = -484 Y = -524 16782 0 3 0

Z = -13852 Z = -12643 528 -1 0 2Reference Point Description: Center of interface plane with WIF



7-25




Element Properties: Destiny Lab moduleMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = 6314 -41653 N/A N/A N/AN/A Y = N/A Y = 0 -711 N/A N/A N/A

Z = N/A Z = 4850 4 N/A N/A N/AReference Point Description: Center of forward CBM interface plane



7-26




Element Properties: PMA 2 (on Destiny Lab forward CBM)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 7437 X = 8704 -44043 978 -27 -2371164 Y = 16 Y = 1 -1421 -27 1273 -4

Z = 5279 Z = 5560 3 -237 -4 1204Reference Point Description: Center of forward APAS interface plane



7-27




Element Properties: Destiny Lab PDGF Rigid UmbilicalMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = 5589 -40928 N/A N/A N/AN/A Y = N/A Y = -216 -2934 N/A N/A N/A

Z = N/A Z = 7073 220 N/A N/A N/AReference Point Description: Starboard, forward, zenith corner of the umbilicals



7-28




Element Properties: LCAMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = 814 -36153 N/A N/A N/AN/A Y = N/A Y = 0 1588 N/A N/A N/A

Z = N/A Z = 2551 4 N/A N/A N/AReference Point Description: Center of nadir LCA base



7-29




Element Properties: PMA 3 (on Unity Node 1 port CBM, rotated for orbiter tail nadir docking)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4440 X = -4463 -30876 1246 23 -41168 Y = -3115 Y = -1992 -708 23 991 220

Z = 5279 Z = 4847 1996 -4 221 1186Reference Point Description: Center of starboard CBM interface



7-30




Element Properties: Destiny Lab UHF AntennaMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 5591 X = 5578 -40917 23 0 043 Y = 2954 Y = 1654 -2139 0 23 0

Z = 7435 Z = 6278 -1650 0 0 0Reference Point Description: Center of base interface



7-31




Element Properties: ESP1, with Destiny Lab DCSU and one PFCSMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -153 X = -1584 -33755 84 19 0503 Y = -2978 Y = -2354 -1067 19 297 0

Z = 5205 Z = 5206 2358 0 0 271Reference Point Description: Center of interface plane with trunnion pin



7-32




Element Properties: Space Station RMS (on Destiny Lab PDGFs, tilted for Orbiter arrival / departure)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 73 X = 3516 -38855 8503 -366 37851502 Y = -710 Y = -1439 -2588 -366 10308 2238

Z = 8583 Z = 6727 1443 3785 2238 12937Reference Point Description: Center of nadir PDGF interface



7-33




Element Properties: S-band Antenna (stowed on Z1, spare)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4525 X = N/A N/A 18 1 0103 Y = 2562 Y = N/A N/A 1 18 5

Z = 1604 Z = N/A N/A 0 5 7Reference Point Description: N/A



7-34

CONFIGURATION 086

STEP 001



Element Properties: Airlock Core, with external equipmentMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4395 X = -4463 -30876 18245 714 1117170 Y = 3907 Y = 7567 6695 714 12247 116

Z = 4879 Z = 4851 -7563 12247 116 18024Reference Point Description: Center of starboard crew lock end face



7-35




Element Properties: HPGA-1Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -6574 X = -6822 -28517 199 0 -5550 Y = 3512 Y = 4362 -2556 0 0 0

Z = 6501 Z = 6695 -4358 -5 0 196Reference Point Description: Center of HPGA grapple fixture pin base plane



7-36

CONFIGURATION 086

STEP 001



Element Properties: Airlock Assembly (Airlock Core with external equipment plus 4 HPGA and 2 Misse units)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4411 X = -4463 -30876 30145 759 -29889468 Y = 3812 Y = 7567 -712 759 28161 -615

Z = 5138 Z = 4851 -7563 -2988 -615 23747Reference Point Description: Center of starboard crew lock end face



7-37

CONFIGURATION 086

STEP 001



Element Properties: Early Ammonia Servicer (EAS) [on P6]Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -1998 X = -2331 -33008 162 1 5650 Y = 148 Y = 362 7489 1 240 -19

Z = -4563 Z = -3350 -358 5 -19 136Reference Point Description: Center of interface plane with scuff plate



7-38

CONFIGURATION 086

STEP 001



Element Properties: MISSE (on Airlock HPGA)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4524 X = -4593 -30746 3 0 034 Y = 3347 Y = 3665 -4291 0 2 0

Z = 8724 Z = 8430 -3661 0 0 1Reference Point Description: Forward, port, zenith corner of MISSE



7-39

CONFIGURATION 086

STEP 001



Element Properties: Pirs DC1 Assembly (deployed BPM Ladder & Strela 1 and 2)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -23683 X = -23701 -11638 6525 384 533311 Y = 27 Y = 4 -1124 384 5725 -213

Z = 7443 Z = 5263 0 53 -213 3643Reference Point Description: Center of zenith docking interface plane



7-40

CONFIGURATION 086

STEP 001



Element Properties: Strela 1 Cargo Boom (on DC1)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -23910 X = -23939 -11400 122 1 6174 Y = 1841 Y = 1407 -4201 1 103 -9

Z = 7743 Z = 8340 -1403 6 -9 24Reference Point Description: Center of grapple fixture interface plane



7-41




Element Properties: Biological Production Module (BPM) Ladder (with two BPM foot restraints)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = -24874 -10465 N/A N/A N/AN/A Y = N/A Y = 527 -2743 N/A N/A N/A

Z = N/A Z = 6882 -523 N/A N/A N/AReference Point Description: Center of zenith docking interface plane with Pirs DC 1



7-42

CONFIGURATION 086

STEP 001



Element Properties: SEEDs 3Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = -31695 -3644 N/A N/A N/AN/A Y = N/A Y = -2316 -3382 N/A N/A N/A

Z = N/A Z = 7521 2320 N/A N/A N/AReference Point Description: Port, forward, nadir corner of SEEDs 3



7-43




Element Properties: 4S Soyuz TM-33 (docked to DC1 nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -23709 X = -23701 -11638 24579 0 06745 Y = 2 Y = 4 -5173 0 23665 0

Z = 13462 Z = 9312 0 0 0 4679Reference Point Description: Center of zenith docking interface plane



7-44




Element Properties: 7P Progress (docked to Service Module aft)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -39610 X = -35689 350 5189 33 -186934 Y = 7 Y = 4 0 33 32151 625

Z = 4138 Z = 4139 0 -18 626 32176Reference Point Description: Center of forward docking interface plane



7-45




Element Properties: MT at Work Site 4Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 1950 X = 2377 -37716 915 0 0828 Y = 2858 Y = 2864 4139 0 437 0

Z = 4 Z = 0 -2860 0 0 599Reference Point Description: Center of the MTSAS on the MBS



7-46




Element Properties: S0 Assembly (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 418 X = 0 -35339 174880 -34 349611290 Y = -330 Y = -4096 6621 867 44609 1560

Z = 279 Z = -2482 4100 -3723 -693 161485Reference Point Description: Center of port, zenith trunnion pin



7-47

CONFIGURATION 086

STEP 001



Element Properties:

Airlock SpurMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -1305 X = -2636 -32703 12 10 -1122 Y = 5590 Y = 4445 373 10 24 -6

Z = 3081 Z = 3766 -4441 -11 -11 24Reference Point Description: Center of interface plane to airlock



7-48

CONFIGURATION 086

STEP 001



Element Properties: EV CPDS (installed on S0)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -365 X = -365 -34974 2 0 024 Y = 4247 Y = 4209 5926 0 1 0

Z = -2753 Z = -1787 -4205 0 0 1Reference Point Description: Center of interface plane with S0



7-49




Element Properties: Zarya FGB Starboard Array (Deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -15103 X = N/A N/A 2065 0 0250 Y = 7044 Y = N/A N/A 0 266 3


Zarya FGB Port Array (Deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -15103 X = N/A N/A 2065 0 0250 Y = -7036 Y = N/A N/A 0 266 -3

Z = 4151 Z = N/A N/A 0 -3 2330Reference Point Description: N/A

Zvezda Service Module Highly Directional (HD) AntennaMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -36072 X = N/A N/A 475 -59 -70298 Y = 1830 Y = N/A N/A -59 97 28

Z = 2649 Z = N/A N/A -70 28 424Reference Point Description: N/A

Zvezda Service Module Starboard Array (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -27666 X = N/A N/A 9436 0 0580 Y = 8084 Y = N/A N/A 0 567 0




7-50




Element Properties: Zvezda Service Module Port Array (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -27696 X = N/A N/A 7965 0 0580 Y = -8076 Y = N/A N/A 0 484 0


P6 POF Solar Array (deployed on P6 starboard until P6 moves to P5 port)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -3882 X = -3879 -31460 171792 -15 -11059 Y = 13614 Y = 1460 18019 -15 8787 -1673

Z = -13721 Z = -13880 -1462 -1 -1673 180359Reference Point Description: Center of PV mast canister interface with beta gimbal

S4 Radiator (on P6 starboard, deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4562 X = N/A N/A 14601 152 3744 Y = 4455 Y = N/A N/A 152 956 -178

Z = -3782 Z = N/A N/A 3 -178 13843Reference Point Description: N/A

P6 Radiator (forward, deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 77 X = N/A N/A 940 149 174731 Y = -17 Y = N/A N/A 149 14346 -3




7-51




Element Properties: S6 Radiator (on P6 aft, deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -9154 X = N/A N/A 956 -152 178744 Y = -17 Y = N/A N/A -152 14601 3

Z = -5581 Z = N/A N/A 178 3 13843Reference Point Description: N/A

P6 Beta Gimbals (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4539 X = N/A N/A 1303 -571 0851 Y = 5 Y = N/A N/A -571 530 0


HPGA-4Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -3043 X = -2876 -32463 195 0 -5565 Y = 3512 Y = 4362 1827 0 136 0


HPGA-2Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -5020 X = -5085 -30254 192 0 -1566 Y = 3512 Y = 4362 -3641 0 136 0




7-52




Element Properties: HPGA-3Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -3204 X = -3057 -32282 195 0 4553 Y = 3512 Y = 4362 -3356 0 136 0

Z = 7217 Z = 7495 -4358 4 0 201Reference Point Description: Center of HPGA grapple fixture pin base plane

MISSE (on airlock handrail)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4775 X = -4701 -30638 2 0 028 Y = 8282 Y = 7989 -69 0 1 0

Z = 4525 Z = 4208 -7985 0 0 1Reference Point Description: Forward, port, zenith corner of MISSE

Strela 2 Cargo Boom (on DC1)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -22721 X = -22930 -12409 116 9 -10174 Y = -1584 Y = -1202 -4001 9 109 5

Z = 7543 Z = 8140 1206 -10 5 24Reference Point Description: Center of grapple fixture interface plane



7-53

Technical Monitor Title T. Farrell/EA4/281-483-8123 International Space Station Program

Approved By Configuration 086 –Step 001 M. Falou/LM/281-333-6326 Flight 3S ISS – After Separation

Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0004

NASA Center/Division Revision Date JSC/Systems Engineering Office Original 5/1/02



7-54

Technical Monitor Title

T. Farrell/EA4/281-483-8123 International Space Station Program Approved By Configuration 086 – Step 001

M. Falou/LM/281-333-6326 Flight 3S ISS – After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-MP0001


Total mass: 330250. lb 149799. kg Center of mass: X Y Z -38.83 .66 9.46 ft -11.84 .20 2.88 m Inertia tensor*: slug*ft**2 3991117. -182272. 2189151. -182272. 21730304. -35157. 2189151. -35157. 19728744. kg*m**2 5411226. -247127. 2968089. -247127. 29462324. -47666. 2968089. -47666. 26748572. Principal moments of inertia (IXX, IYY, IZZ): 3690446. 21733419. 20024893. slug*ft**2 5003726. 29467460. 27150940. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 1.92 -7.77 -.56 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 5.20E+00 -8.46E+00 CPy 1.95E+00 .00E+00 -8.57E+00 CPz 7.38E+00 -3.00E-01 .00E+00 X m Y m Z m CPx .00E+00 1.59E+00 -2.58E+00 CPy 5.95E-01 .00E+00 -2.61E+00 CPz 2.25E+00 -9.14E-02 .00E+00 Projected areas: X Y Z 2479.81 4068.43 10512.53 ft**2 230.38 377.97 976.65 m**2 *Off-diagonal elements are negative integrals



7-55

CONFIGURATION 070

STEP 002

Flight 7P – After Separation


�� Flight 7P [Progress M1-8] undocked from Zvezda Service Module Aft docking

port before 8P Progress launch.

�� 7P Progress vehicle departed after unloading propellant and dry cargo and

loading waste.

Element Properties: ISS Core Assembly - 7P_ASMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -10550 X = N/A N/A 795793 -189014 444976108889 Y = 280 Y = N/A N/A -189014 16576236 -63209




7-56




7-57



M. Falou/LM/281-333-6326 Flight 7P ISS - After Separation Produced By Contract Item Number

NAS9-19100 Science Engineering Analysis & Test 02-DR0005 NASA Center/Division Revision Date

Brad Henry

JSC/Systems Engineering Office Original 5/1/02



7-58



M. Falou/LM/281-333-6326 Flight 7P ISS - After Separation Produced By Contract Item Number

Dean Coleman NAS9-19100 Science Engineering Analysis & Test 02-MP0002 NASA Center/Division Revision Date JSC/Systems Engineering Office Original 5/1/02

Total mass: 314802. lb 142792. kg Center of mass: X Y Z -34.41 .69 9.26 ft -10.49 .21 2.82 m Inertia tensor*: slug*ft**2 3978369. -152857. 2001768. -152857. 17558090. -37033. 2001768. -37033. 15564836. kg*m**2 5393942. -207246. 2714032. -207246. 23805562. -50210. 2714032. -50210. 21103074. Principal moments of inertia (IXX, IYY, IZZ): 3640662. 17561349. 15898132. slug*ft**2 4936226. 23810720. 21555632. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 2.03 -9.53 -.60 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 5.17E+00 -8.27E+00 CPy 3.34E+00 .00E+00 -9.11E+00 CPz 5.23E+00 -5.43E-01 .00E+00 X m Y m Z m CPx .00E+00 1.58E+00 -2.52E+00 CPy 1.02E+00 .00E+00 -2.78E+00 CPz 1.59E+00 -1.66E-01 .00E+00 Projected areas: X Y Z 2479.11 3823.70 10269.82 ft**2 230.32 355.23 954.10 m**2 *Off-diagonal elements are negative integrals



7-59

CONFIGURATION 071

STEP 003

Flight 8P – After Rendezvous


�� Flight 8P [Progress M-46] vehicle launched and delivered to orbit by Soyuz launch

vehicle.

�� Eighth Progress vehicle of the ISS assembly sequence docked to Zvezda Service

Module aft docking port with solar arrays clocked 45 degrees.


X = -39610 X = -35689 350 5189 33 -186934 Y = 7 Y = 4 0 33 32151 625




7-60




7-61



M. Falou/LM/281-333-6326 Flight 8P ISS – After Rendezvous Produced By Contract Item Number


Brad Henry




7-62








7-63

CONFIGURATION 078

STEP 004

Stage UF2 – After Rendezvous

(STS-111 Space Shuttle Endeavour)

�� STS-111 Space Shuttle Endeavour [OV-105] docked to PMA 2, tail nadir.

�� UF2 delivers ITS P6 PDGF, MBS, SMDP and MPLM to outfit ISS. ORBITER ATTACH POINT LOCATION:

For Orbiter attach point location, refer to Table 6.3-1



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M. Falou/LM/281-333-6326 Stage UF2 ISS – After Rendezvous Produced By Contract Item Number





7-66



M. Falou/LM/281-333-6326 State UF2 Orbiter – After Rendezvous Produced By Contract Item Number


Total mass: 243091. lb 110264. kg Center of mass: X Y Z 35.57 -.02 55.09 ft 10.84 -.01 16.79 m Inertia tensor*: slug*ft**2 7987679. 377. 265267. 377. 7680585. -10276. 265267. -10276. 965199. kg*m**2 10829833. 511. 359654. 511. 10413470. -13932. 359654. -13932. 1308633. Principal moments of inertia (IXX, IYY, IZZ): 7997437. 7680362. 955147. slug*ft**2 10843400. 10413491. 1295045. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .09 2.16 .00 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.39E-02 -1.23E+00 CPy -3.63E+00 .00E+00 -1.29E+00 CPz -1.09E+00 2.33E-02 .00E+00 X m Y m Z m CPx .00E+00 7.27E-03 -3.74E-01 CPy -1.11E+00 .00E+00 -3.92E-01 CPz -3.31E-01 7.09E-03 .00E+00 Projected areas: X Y Z 4393.25 2157.96 740.27 ft**2 408.15 200.48 68.77 m**2 *Off-diagonal elements are negative integrals



7-67



M. Falou/LM/281-333-6326 Stage UF2 Mated – After Rendezvous Produced By Contract Item Number


Brad Henry




7-68



M. Falou/LM/281-333-6326 Stage UF2 Mated – After Rendezvous Produced By Contract Item Number


Total mass: 573179. lb 259990. kg Center of mass: X Y Z -7.28 .37 28.81 ft -2.22 .11 8.78 m Inertia tensor*: slug*ft**2 21040292. 39317. -12318119. 39317. 62553984. 89894. -12318119. 89894. 44779404. kg*m**2 28526794. 53307. -16701119. 53307. 84811776. 121880. -16701119. 121880. 60712692. Principal moments of inertia (IXX, IYY, IZZ): 15803040. 62552515. 50014142. slug*ft**2 21426700. 84812416. 67812144. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -.34 23.03 .10 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.94E+00 8.14E+00 CPy -5.67E+00 .00E+00 -9.48E+00 CPz -2.02E+01 2.01E-01 .00E+00 X m Y m Z m CPx .00E+00 5.92E-01 2.48E+00 CPy -1.73E+00 .00E+00 -2.89E+00 CPz -6.16E+00 6.12E-02 .00E+00 Projected areas: X Y Z 5829.24 6220.82 11147.97 ft**2 541.55 577.93 1035.68 m**2 *Off-diagonal elements are negative integrals



7-69

CONFIGURATION 079

STEP 005

Stage UF2 – Intermediate 1


�� Shuttle RMS removes the Leonardo MPLM from the orbiter payload bay and

berths it to the Unity Node 1 nadir CBM.



7-70

CONFIGURATION 079

STEP 005



Element Properties: MPLM (loaded, berthed to Unity nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4570 X = -4463 -30876 39578 8 47110446 Y = 52 Y = -1 -2705 8 38981 1528

Z = 10152 Z = 6844 5 471 1528 29700Reference Point Description: Center of zenith MPLM CBM interface with Unity



7-71



M. Falou/LM/281-333-6326 Stage UF2 ISS – Intermediate 1 Produced By Contract Item Number





7-72



M. Falou/LM/281-333-6326 Stage UF2 Orbiter – Intermediate 1 Produced By Contract Item Number


Total mass: 219977. lb 99780. kg Center of mass: X Y Z 35.76 -.06 54.98 ft 10.90 -.02 16.76 m Inertia tensor*: slug*ft**2 7951047. -164. 262254. -164. 7640941. -9639. 262254. -9639. 940304. kg*m**2 10780167. -222. 355568. -222. 10359720. -13069. 355568. -13069. 1274880. Principal moments of inertia (IXX, IYY, IZZ): 7960598. 7640717. 930464. slug*ft**2 10793451. 10359738. 1261579. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .08 2.14 .09 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 6.32E-02 -1.12E+00 CPy -3.69E+00 .00E+00 -1.29E+00 CPz -1.28E+00 6.26E-02 .00E+00 X m Y m Z m CPx .00E+00 1.93E-02 -3.41E-01 CPy -1.13E+00 .00E+00 -3.92E-01 CPz -3.90E-01 1.91E-02 .00E+00 Projected areas: X Y Z 4393.25 2066.32 740.27 ft**2 408.15 191.97 68.77 m**2 *Off-diagonal elements are negative integrals



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M. Falou/LM/281-333-6326 Stage UF2 Mated – Intermediate 1 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0008




7-74



M. Falou/LM/281-333-6326 Stage UF2 Mated – Intermediate 1 Produced By Contract Item Number





7-75

CONFIGURATION 108

STEP 006



�� Install PDGF on ITS P6.

�� Transfer SMDP kit from the Orbiter payload bay to PMA1. SMDP remains in its

stowed configuration.



7-76

CONFIGURATION 108

STEP 006



Element Properties: P6 PDGFMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -5525 X = -5524 -29815 1 0 033 Y = -1215 Y = -1294 9934 0 2 0

Z = -5797 Z = -5795 1298 0 0 1Reference Point Description: Center of grapple fixture scuff plate



7-77

CONFIGURATION 108

STEP 006



Element Properties: SMDP on PMA-1Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -9579 X = N/A N/A 4 1 150 Y = -496 Y = N/A N/A 1 4 -1




7-78




7-79








7-80








7-81







7-82








7-83

CONFIGURATION 080

STEP 007



�� Shuttle RMS removes the MBS from the Shuttle payload bay and berths it to the MT, which was located at worksite #4.

�� Deploy MBS LEE and camera.

�� Prepare MPLM for return to Orbiter payload bay. Element Properties: MPLM (unloaded, berthed to Unity nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4570 X = -4463 -30876 39578 8 47110446 Y = 52 Y = -1 -2705 8 38981 1528

Z = 10152 Z = 6844 5 471 1528 29700Reference Point Description: Center of zenith MPLM CBM interface with Unity



7-84

CONFIGURATION 080

STEP 007



Element Properties: MBS UF-2 INT3 (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 3225 X = 3372 -38711 2857 -4 731443 Y = 2872 Y = 2870 6997 -4 1004 8

Z = -290 Z = -2858 -2866 73 8 2089Reference Point Description: Center of the keel pin



7-85








7-86








7-87







7-88








7-89

CONFIGURATION 081

STEP 008

Stage UF2 – Before Separation


�� Shuttle RMS removes the Leonardo MPLM from temporary position on Unity

Node 1 nadir CBM and returns it to the Orbiter payload bay.



7-90




7-91



M. Falou/LM/281-333-6326 Stage UF2 ISS – Before Separation Produced By Contract Item Number





7-92



M. Falou/LM/281-333-6326 Stage UF2 Orbiter – Before Separation Produced By Contract Item Number


Total mass: 234894. lb 106546. kg Center of mass: X Y Z 35.62 .00 55.55 ft 10.86 .00 16.93 m Inertia tensor*: slug*ft**2 7745442. 32. 255166. 32. 7437830. -10461. 255166. -10461. 949350. kg*m**2 10501404. 43. 345958. 43. 10084339. -14183. 345958. -14183. 1287145. Principal moments of inertia (IXX, IYY, IZZ): 7754769. 7437616. 939737. slug*ft**2 10514376. 10084362. 1274151. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .09 2.15 .07 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 4.18E-03 -1.69E+00 CPy -3.67E+00 .00E+00 -1.64E+00 CPz -1.13E+00 3.57E-03 .00E+00 X m Y m Z m CPx .00E+00 1.27E-03 -5.16E-01 CPy -1.12E+00 .00E+00 -4.99E-01 CPz -3.45E-01 1.09E-03 .00E+00 Projected areas: X Y Z 4393.25 2148.22 740.27 ft**2 408.15 199.58 68.77 m**2 *Off-diagonal elements are negative integrals



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M. Falou/LM/281-333-6326 Stage UF2 Mated – Before Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0011




7-94



M. Falou/LM/281-333-6326 Stage UF2 Mated – Before Separation Produced By Contract Item Number





7-95

CONFIGURATION 082

STEP 009

Stage UF2 – After Separation


�� STS -111 Space Shuttle Endeavour [OV-105] undocked from ISS.

�� Stage UF2 delivered the Leonardo MPLM to outfit the ISS.

�� MBS was delivered and berthed to the MT.



7-96




7-97



M. Falou/LM/281-333-6326 Stage UF2 ISS - After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0012




7-98



M. Falou/LM/281-333-6326 Stage UF2 ISS - After Separation Produced By Contract Item Number





7-99

CONFIGURATION 106

STEP 010

Flight 4S – After Separation 1

(RSA Flight ID:208)

�� Flight 4S [Soyuz TM-34] vehicle undocked from Pirs DC 1 nadir docking port to

relocate to Zarya FGB.

�� The Relocation of Flight 4S Soyuz is to ensure that 4 Soyuz is on FGB Nadir port

in support of the Orlan based EVAs from the Docking Compartment 1.

Element Properties: SSRMS (installed on MT at Work Site 4)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 5528 X = 3564 -38903 8879 -4325 -8091502 Y = 6687 Y = 4257 5068 -4325 4804 -412

Z = 212 Z = -929 -4253 -809 -412 10140Reference Point Description: Center of nadir PDGF interface



7-100




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M. Falou/LM/281-333-6326 Flight 4S ISS – After Separation 1 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0013




7-102



M. Falou/LM/281-333-6326 Flight 4S ISS – After Separation 1 Produced By Contract Item Number


Total mass: 318583. lb 144507. kg Center of mass: X Y Z -36.33 1.03 7.44 ft -11.07 .31 2.27 m Inertia tensor*: slug*ft**2 3414253. -342980. 1689216. -342980. 20747946. -32964. 1689216. -32964. 19427664. kg*m**2 4629103. -465018. 2290269. -465018. 28130424. -44693. 2290269. -44693. 26340364. Principal moments of inertia (IXX, IYY, IZZ): 3231390. 20757862. 19599259. slug*ft**2 4381311. 28144742. 26573840. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 3.27 -5.95 -1.11 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 6.57E+00 -1.09E+01 CPy 1.79E+00 .00E+00 -8.84E+00 CPz 5.42E+00 -4.37E-01 .00E+00 X m Y m Z m CPx .00E+00 2.00E+00 -3.31E+00 CPy 5.47E-01 .00E+00 -2.70E+00 CPz 1.65E+00 -1.33E-01 .00E+00 Projected areas: X Y Z 2120.55 3944.07 10618.23 ft**2 197.01 366.42 986.47 m**2 *Off-diagonal elements are negative integrals



7-103

CONFIGURATION 107

STEP 011

Flight 4S – After Rendezvous 2


�� Flight 4S [Soyuz TM-34] vehicle docked to Zarya FGB nadir port.

�� The Relocation of Flight 4S Soyuz is to ensure that 4 Soyuz is on FGB Nadir port

in support of the Orlan based EVAs from the Docking Compartment 1.

�� Soyuz vehicle is clocked 45 degrees.

�� Prior to this configuration, SSRMS is relocated from Destiny Lab module to MBS.



7-104

CONFIGURATION 107

STEP 011

Flight 4S – After Rendezvous 2


Element Properties: SMDP on SM (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -27171 X = N/A N/A 1256 0 050 Y = 4 Y = N/A N/A 0 697 0

Z = 4139 Z = N/A N/A 0 0 1820Reference Point Description: Forward port corner of SMDP

4S Soyuz (docked to FGB nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -11136 X = -11118 -24221 23811 443 06745 Y = 3 Y = 4 -1140 443 23811 0




7-105



M. Falou/LM/281-333-6326 Flight 4S ISS – After Rendezvous 2 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0014




7-106



M. Falou/LM/281-333-6326 Flight 4S ISS – After Rendezvous 2 Produced By Contract Item Number


Total mass: 333453. lb 151252. kg Center of mass: X Y Z -36.36 .99 8.49 ft -11.08 .30 2.59 m Inertia tensor*: slug*ft**2 3677030. -342966. 1692266. -342966. 21019298. -22365. 1692266. -22365. 19442256. kg*m**2 4985381. -465000. 2294403. -465000. 28498330. -30323. 2294403. -30323. 26360148. Principal moments of inertia (IXX, IYY, IZZ): 3490773. 21027620. 19618825. slug*ft**2 4732998. 28510496. 26600368. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 2.26 -6.05 -1.11 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 4.72E+00 -8.75E+00 CPy 1.56E+00 .00E+00 -8.03E+00 CPz 5.11E+00 -3.95E-01 .00E+00 X m Y m Z m CPx .00E+00 1.44E+00 -2.67E+00 CPy 4.77E-01 .00E+00 -2.45E+00 CPz 1.56E+00 -1.20E-01 .00E+00 Projected areas: X Y Z 2530.08 4167.03 10688.14 ft**2 235.05 387.13 992.96 m**2 *Off-diagonal elements are negative integrals



7-107

CONFIGURATION 076

STEP 012



�� Flight 8P [Progress M1-46] vehicle undocked from Service Module aft docking

port before 9P Progress launch.


loading waste.


X = -10530 X = N/A N/A 795049 -188041 444243108678 Y = 280 Y = N/A N/A -188041 16564978 -63562




7-108




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M. Falou/LM/281-333-6326 Flight 8P ISS – After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0015




7-110



M. Falou/LM/281-333-6326 Flight 8P ISS – After Separation Produced By Contract Item Number


Total mass: 317701. lb 144107. kg Center of mass: X Y Z -31.81 1.03 8.24 ft -9.69 .31 2.51 m Inertia tensor*: slug*ft**2 3659073. -297313. 1452499. -297313. 16609004. -25534. 1452499. -25534. 15044701. kg*m**2 4961035. -403102. 1969324. -403102. 22518776. -34619. 1969324. -34619. 20397866. Principal moments of inertia (IXX, IYY, IZZ): 3470106. 16617767. 15223812. slug*ft**2 4704976. 22531356. 20641348. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 2.41 -7.15 -1.28 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 4.67E+00 -8.51E+00 CPy 2.86E+00 .00E+00 -8.54E+00 CPz 2.76E+00 -6.47E-01 .00E+00 X m Y m Z m CPx .00E+00 1.42E+00 -2.59E+00 CPy 8.71E-01 .00E+00 -2.60E+00 CPz 8.41E-01 -1.97E-01 .00E+00 Projected areas: X Y Z 2529.39 3920.85 10458.39 ft**2 234.99 364.26 971.62 m**2 *Off-diagonal elements are negative integrals



7-111

CONFIGURATION 077

STEP 013

Flight 9P - After Rendezvous


�� Flight 9P [Progress M-9] vehicle launched and delivered to orbit by Soyuz launch

vehicle.

�� Nineth Progress vehicle of ISS assembly sequence docked to Zvezda Service

Module aft docking port with Solar Arrays clocked 45 degrees.


X = -39610 X = -35689 350 5189 33 -186934 Y = 7 Y = 4 0 33 32151 626




7-112




7-113



M. Falou/LM/281-333-6326 Flight 9P ISS - After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 09-DR0016




7-114



M. Falou/LM/281-333-6326 Flight 9P ISS - After Rendezvous Produced By Contract Item Number


Total mass: 332988. lb 151041. kg Center of mass: X Y Z -36.31 .99 8.48 ft -11.07 .30 2.59 m Inertia tensor*: slug*ft**2 3676281. -342217. 1690000. -342217. 21012470. -22629. 1690000. -22629. 19435726. kg*m**2 4984366. -463984. 2291332. -463984. 28489070. -30681. 2291332. -30681. 26351294. Principal moments of inertia (IXX, IYY, IZZ): 3490463. 21020775. 19611871. slug*ft**2 4732577. 28501216. 26590940. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 2.27 -6.05 -1.11 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 4.72E+00 -8.75E+00 CPy 1.52E+00 .00E+00 -8.02E+00 CPz 5.07E+00 -3.95E-01 .00E+00 X m Y m Z m CPx .00E+00 1.44E+00 -2.67E+00 CPy 4.63E-01 .00E+00 -2.45E+00 CPz 1.54E+00 -1.21E-01 .00E+00 Projected areas: X Y Z 2530.08 4167.03 10688.14 ft**2 235.05 387.13 992.96 m**2 *Off-diagonal elements are negative integrals



7-115

CONFIGURATION 087

STEP 014

Stage 9A – After Rendezvous

(STS 112 on Space Shuttle Atlantis)

�� STS-112 Space Shuttle Atlantis [OV-104] docked to PMA 2, tail nadir.

�� Stage 9A delivers the ITS S1 Assembly including the following: S1 ITS, S-band

Antenna, CETA Cart A, CETA lights, S1 EATCS Radiator.

ORBITER ATTACH POINT LOCATION:

For Orbiter attach point location, refer to Table 6.3-1.



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7-117



M. Falou/LM/281-333-6326 Stage 9A ISS – After Rendezvous Produced By Contract Item Number


Total mass: 332988. lb 151041. kg Center of mass: X Y Z -36.31 .32 8.48 ft -11.07 .10 2.59 m Inertia tensor*: slug*ft**2 3670537. -5230. 1690000. -5230. 21012470. -81664. 1690000. -81664. 19429982. kg*m**2 4976578. -7090. 2291332. -7090. 28489070. -110722. 2291332. -110722. 26343506. Principal moments of inertia (IXX, IYY, IZZ): 3491235. 21016569. 19603820. slug*ft**2 4733624. 28495512. 26580024. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 3.32 -6.05 .01 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 4.66E+00 -8.79E+00 CPy 1.52E+00 .00E+00 -8.02E+00 CPz 5.01E+00 -1.19E-01 .00E+00 X m Y m Z m CPx .00E+00 1.42E+00 -2.68E+00 CPy 4.63E-01 .00E+00 -2.45E+00 CPz 1.53E+00 -3.64E-02 .00E+00 Projected areas: X Y Z 2500.32 4167.03 10682.40 ft**2 232.29 387.13 992.43 m**2 *Off-diagonal elements are negative integrals



7-118



M. Falou/LM/281-333-6326 Stage 9A Orbiter – After Rendezvous Produced By Contract Item Number


Total mass: 243156. lb 110294. kg Center of mass: X Y Z 35.62 -.02 54.84 ft 10.86 -.01 16.71 m Inertia tensor*: slug*ft**2 8009516. 471. 218639. 471. 7722514. -5557. 218639. -5557. 957117. kg*m**2 10859440. 639. 296435. 639. 10470318. -7534. 296435. -7534. 1297676. Principal moments of inertia (IXX, IYY, IZZ): 8016039. 7722279. 950311. slug*ft**2 10868622. 10470324. 1288489. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .05 1.77 -.06 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.39E-02 -9.77E-01 CPy -3.65E+00 .00E+00 -1.31E+00 CPz -1.14E+00 2.33E-02 .00E+00 X m Y m Z m CPx .00E+00 7.27E-03 -2.98E-01 CPy -1.11E+00 .00E+00 -3.98E-01 CPz -3.47E-01 7.09E-03 .00E+00 Projected areas: X Y Z 4393.25 2148.04 740.27 ft**2 408.15 199.56 68.77 m**2 *Off-diagonal elements are negative integrals



7-119



M. Falou/LM/281-333-6326 Stage 9A Mated – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0017




7-120



M. Falou/LM/281-333-6326 Stage 9A Mated – After Rendezvous Produced By Contract Item Number


Total mass: 576144. lb 261335. kg Center of mass: X Y Z -5.95 .18 28.05 ft -1.81 .05 8.55 m Inertia tensor*: slug*ft**2 21065690. 102082. -12656004. 102082. 60722764. -18376. -12656004. -18376. 42990252. kg*m**2 28561228. 138404. -17159230. 138404. 82328976. -24914. -17159230. -24914. 58286928. Principal moments of inertia (IXX, IYY, IZZ): 15283800. 60721334. 48769703. slug*ft**2 20722684. 82329592. 66124860. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .23 24.55 .12 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.82E+00 8.08E+00 CPy -5.99E+00 .00E+00 -9.46E+00 CPz -2.15E+01 2.37E-01 .00E+00 X m Y m Z m CPx .00E+00 5.56E-01 2.46E+00 CPy -1.83E+00 .00E+00 -2.88E+00 CPz -6.54E+00 7.23E-02 .00E+00 Projected areas: X Y Z 6014.38 6312.30 11285.36 ft**2 558.75 586.43 1048.44 m**2 *Off-diagonal elements are negative integrals



7-121

CONFIGURATION 088

STEP 015

Stage 9A – Intermediate 1

(STS-112 Space Shuttle Atlantis)

�� The Shuttle RMS removes ITS S1 from the Orbiter payload bay and attachs it to

the starboard interface of S0.



7-122

CONFIGURATION 088

STEP 015



Element Properties: S1 stowed (with CETA Cart A)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 78 X = 0 -35339 181036 12516 93112747 Y = 13330 Y = 9168 6622 12516 27311 -1379

Z = 67 Z = -2483 -9164 931 -1379 160891Reference Point Description: Center of the port keel pin



7-123



M. Falou/LM/281-333-6326 Stage 9A ISS – Intermediate 1 Produced By Contract Item Number


Total mass: 361090. lb 163788. kg Center of mass: X Y Z -33.47 3.70 7.84 ft -10.20 1.13 2.39 m Inertia tensor*: slug*ft**2 5377260. -1274737. 1934094. -1274737. 22164676. 206305. 1934094. 206305. 22143892. kg*m**2 7290582. -1728311. 2622279. -1728311. 30051252. 279712. 2622279. 279712. 30023074. Principal moments of inertia (IXX, IYY, IZZ): 5059617. 22233084. 22391590. slug*ft**2 6860130. 30144936. 30359848. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 24.45 -6.49 -4.34 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 9.23E+00 -8.06E+00 CPy -1.29E+00 .00E+00 -7.38E+00 CPz 2.21E+00 -3.45E+00 .00E+00 X m Y m Z m CPx .00E+00 2.81E+00 -2.46E+00 CPy -3.94E-01 .00E+00 -2.25E+00 CPz 6.72E-01 -1.05E+00 .00E+00 Projected areas: X Y Z 3130.98 4171.00 10693.54 ft**2 290.88 387.50 993.46 m**2 *Off-diagonal elements are negative integrals



7-124



M. Falou/LM/281-333-6326 Stage 9A Orbiter – Intermediate 1 Produced By Contract Item Number





7-125



M. Falou/LM/281-333-6326 Stage 9A Mated – Intermediate 1 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0018




7-126



M. Falou/LM/281-333-6326 Stage 9A Mated – Intermediate 1 Produced By Contract Item Number


Total mass: 576131. lb 261329. kg Center of mass: X Y Z -7.54 2.30 25.71 ft -2.30 .70 7.84 m Inertia tensor*: slug*ft**2 22870040. -183931. -11752554. -183931. 59521404. 950350. -11752554. 950350. 43349572. kg*m**2 31007598. -249377. -15934317. -249377. 80700152. 1288502. -15934317. 1288502. 58774104. Principal moments of inertia (IXX, IYY, IZZ): 17520379. 59601997. 48614752. slug*ft**2 23755170. 80811928. 65914768. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -5.07 24.48 .34 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.70E+00 7.03E+00 CPy -4.96E+00 .00E+00 -7.54E+00 CPz -1.98E+01 -1.84E+00 .00E+00 X m Y m Z m CPx .00E+00 1.13E+00 2.14E+00 CPy -1.51E+00 .00E+00 -2.30E+00 CPz -6.05E+00 -5.60E-01 .00E+00 Projected areas: X Y Z 6639.31 6231.94 11297.37 ft**2 616.81 578.97 1049.56 m**2 *Off-diagonal elements are negative integrals



7-127

CONFIGURATION 089

STEP 016

Stage 9A – Before Separation


�� Install external cameras and stantions on Destiny Lab [port 13] and S1 truss

outboard lower [port 3].

�� Deploy S-Band antenna on S1 truss.

�� Deploy S1 EATCS center radiator.

�� Deploy CETA cart A on starboard side of MT.

�� Deploy and install CETA light stanchion and lights on S1 truss.

�� Remove and stow S1 truss inboard and outboard keel pins.

�� Transfer OTD from PMA1 and ETSD #2 [starboard] from Z1 to CETA cart A.

�� Transfer APFR and tool stanchion to CETA cart A.



7-128

CONFIGURATION 089

STEP 016



Element Properties: CETA Cart A with ETSDMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 1972 X = 2337 -37676 229 0 -26350 Y = 6074 Y = 5629 2611 0 185 2

Z = 41 Z = 1528 -5625 -26 2 61Reference Point Description: Port, forward, nadir corner of the ETSD



7-129

CONFIGURATION 089

STEP 016


(STS-112 Space Shuttle Atlantis) Element Properties: S1 with EATCS radiator (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -741 X = 0 -35339 16776 -22185 -24512505 Y = 13417 Y = 9168 6622 -22185 186419 480

Z = 14 Z = -2483 -9164 -245 480 329126Reference Point Description: Center of port, zenith trunnion pin



7-130

CONFIGURATION 089

STEP 016



Element Properties: EATCS Radiator with support structure (deployed on S1)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -2684 X = -107 -35232 54183 -41 -2805095 Y = 14699 Y = 14692 4139 -41 141401 -47

Z = 24 Z = 0 -14688 -280 -47 183707Reference Point Description: Center of the thermal radiator rotary joint



7-131

CONFIGURATION 089

STEP 016



Element Properties: ETSD (installed on CETA cart A)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 2166 X = 1995 -37334 11 0 0108 Y = 6065 Y = 6496 3282 0 5 0

Z = 1193 Z = 857 -6492 0 0 8Reference Point Description: Starboard, aft, zenith corner of ETSD



7-132




7-133



M. Falou/LM/281-333-6326 Stage 9A ISS – Before Separation Produced By Contract Item Number


Total mass: 361090. lb 163788. kg Center of mass: X Y Z -33.64 4.31 7.83 ft -10.25 1.31 2.39 m Inertia tensor*: slug*ft**2 5329358. -1495090. 1921927. -1495090. 22152948. 266797. 1921927. 266797. 22096524. kg*m**2 7225635. -2027069. 2605782. -2027069. 30035350. 361728. 2605782. 361728. 29958850. Principal moments of inertia (IXX, IYY, IZZ): 4977974. 22202082. 22397240. slug*ft**2 6749433. 30102902. 30367508. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 40.41 -6.46 -5.08 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 8.98E+00 -8.01E+00 CPy -1.08E+00 .00E+00 -7.40E+00 CPz 1.49E+00 -1.26E+00 .00E+00 X m Y m Z m CPx .00E+00 2.74E+00 -2.44E+00 CPy -3.30E-01 .00E+00 -2.26E+00 CPz 4.54E-01 -3.83E-01 .00E+00 Projected areas: X Y Z 3117.65 4205.20 11274.05 ft**2 289.64 390.68 1047.39 m**2 *Off-diagonal elements are negative integrals



7-134



M. Falou/LM/281-333-6326 Stage 9A Orbiter – Before Separation Produced By Contract Item Number





7-135



M. Falou/LM/281-333-6326 Stage 9A Mated – Before Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0019




7-136



M. Falou/LM/281-333-6326 Stage 9A Mated – Before Separation Produced By Contract Item Number


Total mass: 574368. lb 260529. kg Center of mass: X Y Z -7.79 2.70 25.64 ft -2.38 .82 7.81 m Inertia tensor*: slug*ft**2 22805386. -236882. -11746519. -236882. 59452364. 1127635. -11746519. 1127635. 43296192. kg*m**2 30919938. -321169. -15926134. -321169. 80606544. 1528867. -15926134. 1528867. 58701728. Principal moments of inertia (IXX, IYY, IZZ): 17461923. 59567693. 48520429. slug*ft**2 23675912. 80765416. 65786880. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -6.03 24.46 .38 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.45E+00 7.18E+00 CPy -4.80E+00 .00E+00 -7.58E+00 CPz -2.05E+01 3.91E-01 .00E+00 X m Y m Z m CPx .00E+00 1.05E+00 2.19E+00 CPy -1.46E+00 .00E+00 -2.31E+00 CPz -6.25E+00 1.19E-01 .00E+00 Projected areas: X Y Z 6627.53 6267.49 11891.57 ft**2 615.72 582.27 1104.76 m**2 *Off-diagonal elements are negative integrals



7-137

CONFIGURATION 090

STEP 017

Stage 9A – After Separation

(STS – 112 on Space Shuttle Atlantis)

�� STS-112 Space Shuttle Atlantis [OV-104] undocked from PMA2 docking port.

�� Stage 9A delivered ITS S1, S-band Antenna, CETA Cart A, CETA Lights, S1

EATCS Radiator.

�� S1 EATCS center radiator was deployed.

�� CETA Cart was installed on MT.

�� ETSD, OTD and APFR were transferred to CETA cart A.



7-138




7-139



M. Falou/LM/281-333-6326 Stage 9A ISS – After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0020




7-140



M. Falou/LM/281-333-6326 Stage 9A ISS – After Separation Produced By Contract Item Number


Total mass: 361090. lb 163788. kg Center of mass: X Y Z -33.64 4.31 7.83 ft -10.25 1.31 2.39 m Inertia tensor*: slug*ft**2 5329358. -1495090. 1921927. -1495090. 22152948. 266797. 1921927. 266797. 22096524. kg*m**2 7225635. -2027069. 2605782. -2027069. 30035350. 361728. 2605782. 361728. 29958850. Principal moments of inertia (IXX, IYY, IZZ): 4977974. 22202082. 22397240. slug*ft**2 6749433. 30102902. 30367508. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 40.41 -6.46 -5.08 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 8.98E+00 -8.01E+00 CPy -1.08E+00 .00E+00 -7.40E+00 CPz 1.49E+00 -1.26E+00 .00E+00 X m Y m Z m CPx .00E+00 2.74E+00 -2.44E+00 CPy -3.30E-01 .00E+00 -2.26E+00 CPz 4.54E-01 -3.83E-01 .00E+00 Projected areas: X Y Z 3117.65 4205.20 11274.05 ft**2 289.64 390.68 1047.39 m**2 *Off-diagonal elements are negative integrals



7-141

CONFIGURATION 102

STEP 018



�� STS-113 Space Shuttle Endeavour [OV-105] docked to PMA 2, tail nadir.

�� Stage 11A delivers the ITS P1 Assembly including the following: P1 truss

segment, WETAs and stanchions, P1 EATCS Radiator, CETA Cart B, APFR, and

UHF antenna.

�� Prior to this configuration:

o MT was relocated to worksite #5.

o MPAC/SEED panel 1 was removed

o Panels 2 and 3 were reconfigured on the support structure.

ORBITER ATTACH POINT LOCATION: For Orbiter attach point location, refer to Table 6.3-1



7-142

CONFIGURATION 102

STEP 018



Element Properties: SEEDs 2Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = N/A X = -31622 -3717 N/A N/A N/AN/A Y = N/A Y = -3245 -2377 N/A N/A N/A

Z = N/A Z = 6516 3249 N/A N/A N/AReference Point Description: Port, forward, nadir corner of SEEDs 2



7-143


T. Farrell/EA4/281-483-8123 International Space Station Program Approved By Configuration 102 - Step 018



Total mass: 361090. lb 163788. kg Center of mass: X Y Z -33.67 3.41 7.84 ft -10.26 1.04 2.39 m Inertia tensor*: slug*ft**2 5473828. -1020444. 1913403. -1020444. 22123866. 195673. 1913403. 195673. 22215340. kg*m**2 7421511. -1383536. 2594225. -1383536. 29995920. 265297. 2594225. 265297. 30119944. Principal moments of inertia (IXX, IYY, IZZ): 5194373. 22162752. 22454368. slug*ft**2 7042840. 30049576. 30444966. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 16.21 -6.44 -3.52 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 8.48E+00 -7.98E+00 CPy -1.37E+00 .00E+00 -7.41E+00 CPz 1.54E+00 -9.50E-01 .00E+00 X m Y m Z m CPx .00E+00 2.59E+00 -2.43E+00 CPy -4.17E-01 .00E+00 -2.26E+00 CPz 4.70E-01 -2.89E-01 .00E+00 Projected areas: X Y Z 3216.81 4183.94 11287.90 ft**2 298.85 388.70 1048.68 m**2 *Off-diagonal elements are negative integrals



7-144





Total mass: 243449. lb 110427. kg Center of mass: X Y Z 35.56 -.03 54.81 ft 10.84 -.01 16.71 m Inertia tensor*: slug*ft**2 8132962. -23019. 214757. -23019. 7769732. -36692. 214757. -36692. 1031545. kg*m**2 11026810. -31209. 291171. -31209. 10534337. -49747. 291171. -49747. 1398586. Principal moments of inertia (IXX, IYY, IZZ): 8140765. 7768115. 1024832. slug*ft**2 11037733. 10532472. 1389528. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .19 1.75 3.72 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.37E-02 -9.48E-01 CPy -3.59E+00 .00E+00 -1.25E+00 CPz -1.08E+00 3.31E-02 .00E+00 X m Y m Z m CPx .00E+00 1.03E-02 -2.89E-01 CPy -1.09E+00 .00E+00 -3.82E-01 CPz -3.29E-01 1.01E-02 .00E+00 Projected areas: X Y Z 4393.25 2149.47 740.27 ft**2 408.15 199.69 68.77 m**2 *Off-diagonal elements are negative integrals



7-145







7-146





Total mass: 604539. lb 274214. kg Center of mass: X Y Z -5.79 2.02 26.76 ft -1.76 .62 8.16 m Inertia tensor*: slug*ft**2 23629234. 32093. -12567116. 32093. 61524812. 888621. -12567116. 888621. 44962460. kg*m**2 32036926. 43512. -17038714. 43512. 83416408. 1204808. -17038714. 1204808. 60960884. Principal moments of inertia (IXX, IYY, IZZ): 17807991. 61584781. 50719702. slug*ft**2 24145132. 83500304. 68768784. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -4.44 24.85 .58 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.56E+00 5.59E+00 CPy -6.37E+00 .00E+00 -8.23E+00 CPz -2.25E+01 5.08E-01 .00E+00 X m Y m Z m CPx .00E+00 1.09E+00 1.71E+00 CPy -1.94E+00 .00E+00 -2.51E+00 CPz -6.86E+00 1.55E-01 .00E+00 Projected areas: X Y Z 6728.27 6331.29 11901.26 ft**2 625.08 588.20 1105.66 m**2 *Off-diagonal elements are negative integrals



7-147

CONFIGURATION 103

STEP 019



�� Space Station RMS removes ITS P1 from the Orbiter payload bay and attaches it

to the port interface of ITS S0.



7-148

CONFIGURATION 103

STEP 019



Element Properties: P1 stowed (with CETA Cart B)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 76 X = 0 -35339 231500 -3175 -93112629 Y = -13358 Y = -17760 6622 -3175 29016 -1050

Z = -41 Z = -2483 17770 -931 -1050 224380Reference Point Description: Center of port, zenith trunnion pin



7-149





Total mass: 388931. lb 176416. kg Center of mass: X Y Z -31.24 .03 7.27 ft -9.52 .01 2.22 m Inertia tensor*: slug*ft**2 7487993. 264225. 2130068. 264225. 23120558. -107787. 2130068. -107787. 25097310. kg*m**2 10152350. 358241. 2887983. 358241. 31347254. -146140. 2887983. -146140. 34027368. Principal moments of inertia (IXX, IYY, IZZ): 7229010. 23122035. 25353092. slug*ft**2 9801521. 31350228. 34375228. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -1.83 -6.80 1.00 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.39E+00 -7.45E+00 CPy -3.78E+00 .00E+00 -6.84E+00 CPz -3.07E-01 1.69E+00 .00E+00 X m Y m Z m CPx .00E+00 1.03E+00 -2.27E+00 CPy -1.15E+00 .00E+00 -2.08E+00 CPz -9.34E-02 5.15E-01 .00E+00 Projected areas: X Y Z 3764.49 4185.92 11472.62 ft**2 349.73 388.89 1065.84 m**2 *Off-diagonal elements are negative integrals



7-150





Total mass: 215607. lb 97798. kg Center of mass: X Y Z 35.94 -.05 55.68 ft 10.96 -.02 16.97 m Inertia tensor*: slug*ft**2 7917026. -24178. 236549. -24178. 7550676. -38543. 236549. -38543. 1001695. kg*m**2 10734041. -32781. 320717. -32781. 10237337. -52257. 320717. -52257. 1358116. Principal moments of inertia (IXX, IYY, IZZ): 7926589. 7548931. 993366. slug*ft**2 10747340. 10235289. 1346864. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .20 1.97 3.88 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 5.34E-02 -1.82E+00 CPy -3.87E+00 .00E+00 -1.87E+00 CPz -1.46E+00 5.28E-02 .00E+00 X m Y m Z m CPx .00E+00 1.63E-02 -5.56E-01 CPy -1.18E+00 .00E+00 -5.71E-01 CPz -4.45E-01 1.61E-02 .00E+00 Projected areas: X Y Z 4393.25 2056.59 740.27 ft**2 408.15 191.06 68.77 m**2 *Off-diagonal elements are negative integrals



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7-152





Total mass: 604539. lb 274214. kg Center of mass: X Y Z -7.28 .00 24.54 ft -2.22 .00 7.48 m Inertia tensor*: slug*ft**2 25509738. 262062. -11656101. 262062. 60235856. -130467. -11656101. -130467. 45558960. kg*m**2 34586544. 355308. -15803544. 355308. 81668816. -176889. -15803544. -176889. 61769628. Principal moments of inertia (IXX, IYY, IZZ): 20158958. 60240400. 50901130. slug*ft**2 27332712. 81677512. 69014776. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 1.28 24.65 .29 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.70E+00 5.36E+00 CPy -5.44E+00 .00E+00 -6.43E+00 CPz -2.05E+01 1.78E+00 .00E+00 X m Y m Z m CPx .00E+00 5.20E-01 1.63E+00 CPy -1.66E+00 .00E+00 -1.96E+00 CPz -6.25E+00 5.41E-01 .00E+00 Projected areas: X Y Z 7271.60 6248.15 12099.27 ft**2 675.55 580.47 1124.06 m**2 *Off-diagonal elements are negative integrals



7-153

CONFIGURATION 104

STEP 020


(STS-113 Space shuttle Endeavour)

�� Install WETAs and stanchions on Node 1 [port 12] and P1 truss Outboard Upper

[port 8].

�� Deploy P1 EATCS truss center radiator.

�� Remove and stow P1 truss starboard and port keel pins.

�� Deploy and relocate CETA cart B to starboard side of Ceta Cart A.

�� Install APFR and tool stanchion on CETA cart B.

�� Transfer ETSD #1 [port] from Z1 to CETA cart B.

�� Deploy UHF Antenna.



7-154

CONFIGURATION 104

STEP 020



Element properties: P1 deployed with EATCS radiatorMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -761 X = 0 -35339 222947 12564 42812387 Y = -13461 Y = -17760 6622 12564 188538 404

Z = 15 Z = -2483 17770 428 404 377489Reference Point Description: Center of port, zenith trunnion pin



7-155

CONFIGURATION 104

STEP 020



Element properties: EATCS Radiator with support structure (deployed on P1)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -2684 X = -107 -35232 54183 41 2805095 Y = -14699 Y = -14692 4139 41 141401 -47

Z = -24 Z = 0 14696 280 -47 183707Reference Point Description: Center of the thermal radiator rotary joint



7-156

CONFIGURATION 104

STEP 020



Element Properties: CETA Cart BMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 1881 X = 2333 -37672 122 0 -2242 Y = -189 Y = -633 2619 0 77 0

Z = 51 Z = 1520 637 -2 0 47Reference Point Description: Port, forward, nadir corner of the ETSD

ETSD on CETA BMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 2162 X = 1990 -37329 11 0 0108 Y = -203 Y = 228 3290 0 5 0

Z = 1185 Z = 849 -224 0 0 8Reference Point Description: Starboard, zenith corner of the ETSD



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Total mass: 388932. lb 176417. kg Center of mass: X Y Z -31.41 .07 7.29 ft -9.57 .02 2.22 m Inertia tensor*: slug*ft**2 7471289. 139971. 2109617. 139971. 23111522. -96891. 2109617. -96891. 25078124. kg*m**2 10129703. 189775. 2860255. 189775. 31335002. -131367. 2860255. -131367. 34001356. Principal moments of inertia (IXX, IYY, IZZ): 7220401. 23109361. 25329455. slug*ft**2 9789849. 31333044. 34343180. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -2.00 -6.74 .55 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.26E+00 -7.47E+00 CPy -3.56E+00 .00E+00 -6.87E+00 CPz -1.10E+00 -5.25E-01 .00E+00 X m Y m Z m CPx .00E+00 9.95E-01 -2.28E+00 CPy -1.09E+00 .00E+00 -2.09E+00 CPz -3.35E-01 -1.60E-01 .00E+00 Projected areas: X Y Z 3769.94 4193.61 11991.84 ft**2 350.24 389.60 1114.08 m**2 *Off-diagonal elements are negative integrals



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7-159







7-160





Total mass: 603085. lb 273555. kg Center of mass: X Y Z -7.51 .03 24.49 ft -2.29 .01 7.46 m Inertia tensor*: slug*ft**2 25461146. 144982. -11655028. 144982. 60185512. -113566. -11655028. -113566. 45526556. kg*m**2 34520664. 196569. -15802089. 196569. 81600560. -153974. -15802089. -153974. 61725692. Principal moments of inertia (IXX, IYY, IZZ): 20114661. 60186707. 50867788. slug*ft**2 27272652. 81604712. 68969568. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .95 24.64 .13 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.63E+00 5.38E+00 CPy -5.21E+00 .00E+00 -6.41E+00 CPz -2.13E+01 -3.22E-01 .00E+00 X m Y m Z m CPx .00E+00 4.98E-01 1.64E+00 CPy -1.59E+00 .00E+00 -1.96E+00 CPz -6.49E+00 -9.82E-02 .00E+00 Projected areas: X Y Z 7276.61 6255.91 12618.32 ft**2 676.02 581.19 1172.28 m**2 *Off-diagonal elements are negative integrals



7-161

CONFIGURATION 105

STEP 021



�� STS-113 Space Shuttle Endeavour [OV-105] undocked from ISS.

�� Stage 11A delivered ITS P1, P1 EATCS Radiator, WETAs and stanchions,

CETA Cart B, and UHF Antenna.

�� P1 EATCS center radiator was deployed.

�� CETA Cart B was installed on MT.

�� ETSD #1, APFR, and tool stanchion was transferred to CETA Cart B.



7-162




7-163







7-164








7-165

CONFIGURATION 083

STEP 022



�� Flight 9P [Progress M1-9] vehicle undocked from Service Module aft docking port

before 10P Progress launch.

�� 9P Progress departed after unloading propellant and dry cargo and loading

waste.


X = -10570 X = N/A N/A 796751 -191511 445220109162 Y = 280 Y = N/A N/A -191511 16592516 -63462




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7-167







7-168





Total mass: 374712. lb 169967. kg Center of mass: X Y Z -27.48 .07 7.04 ft -8.38 .02 2.15 m Inertia tensor*: slug*ft**2 7450053. 140576. 1810037. 140576. 18302312. -97562. 1810037. -97562. 20287584. kg*m**2 10100911. 190596. 2454079. 190596. 24814592. -132277. 2454079. -132277. 27506258. Principal moments of inertia (IXX, IYY, IZZ): 7197406. 18301166. 20539950. slug*ft**2 9758671. 24813808. 27849284. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -1.87 -7.88 .79 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.26E+00 -7.24E+00 CPy -1.70E+00 .00E+00 -7.38E+00 CPz -3.06E+00 -7.06E-01 .00E+00 X m Y m Z m CPx .00E+00 9.95E-01 -2.21E+00 CPy -5.17E-01 .00E+00 -2.25E+00 CPz -9.34E-01 -2.15E-01 .00E+00 Projected areas: X Y Z 3768.91 3947.07 11742.39 ft**2 350.14 366.70 1090.90 m**2 *Off-diagonal elements are negative integrals



7-169

CONFIGURATION 084

STEP 023



�� Flight 10P [Progress M-47] launched and delivered to orbit by Soyuz launch

vehicle.

�� Tenth progress vehicle of ISS assembly sequence docked to Service Module

aft docking port with Solar Arrays clocked 45 degrees.

Element Properties:

10P Progress (docked to Service Module aft)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -39610 X = -35689 350 5189 33 -186934 Y = 7 Y = 4 0 33 32151 626




7-170




7-171



M. Falou/LM/281-333-6326 Flight 10P ISS – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0026




7-172








7-173

CONFIGURATION 100

STEP 024

Flight 5S – After Rendezvous


�� Flight 5S [Soyuz TMA-1] vehicle docked to Pirs DC 1 nadir docking port.

�� Soyuz vehicle Solar Arrays are not clocked.

�� 5S Soyuz will maintain crew return capability previously assured by the 4S Soyuz

vehicle.

Element Properties: 5S Soyuz (docked to DC1 nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -23709 X = -23701 -11638 24579 0 06745 Y = 2 Y = 4 -5173 0 23665 0




7-174




7-175



M. Falou/LM/281-333-6326 Flight 5S ISS – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0027




7-176



M. Falou/LM/281-333-6326 Flight 5S ISS – After Rendezvous Produced By Contract Item Number


Total mass: 404869. lb 183646. kg Center of mass: X Y Z -33.20 .07 8.65 ft -10.12 .02 2.64 m Inertia tensor*: slug*ft**2 8096612. 137044. 2875402. 137044. 24715600. -95929. 2875402. -95929. 26062290. kg*m**2 10977526. 185807. 3898520. 185807. 33509838. -130062. 3898520. -130062. 35335704. Principal moments of inertia (IXX, IYY, IZZ): 7646067. 24713141. 26513472. slug*ft**2 10366992. 33507544. 35948540. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -2.27 -8.88 .51 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.06E+00 -6.83E+00 CPy -3.18E+00 .00E+00 -6.76E+00 CPz 6.75E-01 -5.26E-01 .00E+00 X m Y m Z m CPx .00E+00 9.33E-01 -2.08E+00 CPy -9.68E-01 .00E+00 -2.06E+00 CPz 2.06E-01 -1.60E-01 .00E+00 Projected areas: X Y Z 4037.35 4352.68 11995.72 ft**2 375.08 404.38 1114.44 m**2 *Off-diagonal elements are negative integrals



7-177

CONFIGURATION 101

STEP 025

Flight 4S – After Separation 2

(RSC Flight ID: 208)

�� Flight 4S [Soyuz TM-34] vehicle undocked from Zarya FGB nadir docking port.

�� 5S Soyuz remains docked to the Pirs DC 1 nadir maintaining crew return

capability previously assured by 3S Soyuz vehicle.



7-178




7-179



M. Falou/LM/281-333-6326 Flight 4S ISS – After Separation 2 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0028




7-180



M. Falou/LM/281-333-6326 Flight 4S ISS – After Separation 2 Produced By Contract Item Number


Total mass: 389999. lb 176901. kg Center of mass: X Y Z -33.07 .07 7.80 ft -10.08 .02 2.38 m Inertia tensor*: slug*ft**2 7840847. 136806. 2839721. 136806. 24454490. -96517. 2839721. -96517. 26053560. kg*m**2 10630756. 185484. 3850143. 185484. 33155822. -130860. 3850143. -130860. 35323868. Principal moments of inertia (IXX, IYY, IZZ): 7406803. 24452296. 26487988. slug*ft**2 10042584. 33153876. 35913988. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -2.03 -8.66 .51 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.13E+00 -6.82E+00 CPy -3.29E+00 .00E+00 -7.55E+00 CPz 5.51E-01 -5.29E-01 .00E+00 X m Y m Z m CPx .00E+00 9.55E-01 -2.08E+00 CPy -1.00E+00 .00E+00 -2.30E+00 CPz 1.68E-01 -1.61E-01 .00E+00 Projected areas: X Y Z 3940.99 4126.02 11982.38 ft**2 366.13 383.32 1113.20 m**2 *Off-diagonal elements are negative integrals



7-181

CONFIGURATION 091

STEP 026

Stage ULF1 – After Rendezvous

(STS – 114 on Space Shuttle Atlantis)

�� STS-114 Space Shuttle Atlantis [OV-104] docked to PMA 2, tail nadir.

�� Stage ULF1 delivers Raffaello MPLM, two WVS stanchions, and ESP-2 with

ORUs to outfit the ISS.

�� Prior to this configuration, the Space Station RMS was relocated from MBS to

Destiny Lab.

ORBITER ATTACH POINT LOCATION: For Orbiter attach point location, refer to Table 6.3-1. Element Properties: Space Station RMS (relocated from MBS to Destiny Lab)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 73 X = 3516 -38855 8503 -366 37851502 Y = -710 Y = -1446 -2235 -366 10308 2238

Z = 8583 Z = 6727 1450 3785 2238 12937Reference Point Description: Center of nadir PDGF interface



7-182




7-183



M. Falou/LM/281-333-6326 Stage ULF1 ISS – After Rendezvous Produced By Contract Item Number


Total mass: 389999. lb 176901. kg Center of mass: X Y Z -33.20 .30 8.03 ft -10.12 .09 2.45 m Inertia tensor*: slug*ft**2 7784927. -7087. 2743962. -7087. 24368300. -72597. 2743962. -72597. 25832644. kg*m**2 10554939. -9608. 3720311. -9608. 33038964. -98428. 3720311. -98428. 35024348. Principal moments of inertia (IXX, IYY, IZZ): 7376729. 24364715. 26242627. slug*ft**2 10001808. 33035128. 35581312. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -2.22 -8.46 .01 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.83E+00 -6.72E+00 CPy -3.06E+00 .00E+00 -7.21E+00 CPz 4.00E-01 -5.70E-01 .00E+00 X m Y m Z m CPx .00E+00 8.62E-01 -2.05E+00 CPy -9.32E-01 .00E+00 -2.20E+00 CPz 1.22E-01 -1.74E-01 .00E+00 Projected areas: X Y Z 3986.29 4160.36 11918.39 ft**2 370.34 386.51 1107.25 m**2 *Off-diagonal elements are negative integrals



7-184



M. Falou/LM/281-333-6326 Stage ULF1 Orbiter – After Rendezvous Produced By Contract Item Number


Total mass: 243789. lb 110581. kg Center of mass: X Y Z 35.72 -.01 54.94 ft 10.89 .00 16.75 m Inertia tensor*: slug*ft**2 7896585. -513. 258692. -513. 7600398. -5898. 258692. -5898. 952674. kg*m**2 10706327. -696. 350739. -696. 10304751. -7997. 350739. -7997. 1291652. Principal moments of inertia (IXX, IYY, IZZ): 7905966. 7600166. 943015. slug*ft**2 10719378. 10304757. 1278596. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .05 2.13 .14 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.73E-02 -1.08E+00 CPy -3.77E+00 .00E+00 -1.08E+00 CPz -1.23E+00 1.67E-02 .00E+00 X m Y m Z m CPx .00E+00 5.27E-03 -3.29E-01 CPy -1.15E+00 .00E+00 -3.30E-01 CPz -3.75E-01 5.09E-03 .00E+00 Projected areas: X Y Z 4393.25 2155.07 740.27 ft**2 408.15 200.21 68.77 m**2 *Off-diagonal elements are negative integrals



7-185



M. Falou/LM/281-333-6326 Stage ULF1 Mated – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0029




7-186



M. Falou/LM/281-333-6326 Stage ULF1 Mated – After Rendezvous Produced By Contract Item Number


Total mass: 633788. lb 287482. kg Center of mass: X Y Z -6.69 .18 26.07 ft -2.04 .05 7.95 m Inertia tensor*: slug*ft**2 25943820. 93802. -12072177. 93802. 64375740. -9468. -12072177. -9468. 48930976. kg*m**2 35175080. 127178. -16367667. 127178. 87281744. -12837. -16367667. -12837. 66341468. Principal moments of inertia (IXX, IYY, IZZ): 20768071. 64374103. 54104047. slug*ft**2 28158584. 87282232. 73357480. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .21 23.20 .12 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.48E+00 3.80E+00 CPy -6.21E+00 .00E+00 -7.06E+00 CPz -2.24E+01 -2.90E-01 .00E+00 X m Y m Z m CPx .00E+00 4.52E-01 1.16E+00 CPy -1.89E+00 .00E+00 -2.15E+00 CPz -6.82E+00 -8.84E-02 .00E+00 Projected areas: X Y Z 7276.46 6311.49 12544.07 ft**2 676.01 586.36 1165.38 m**2 *Off-diagonal elements are negative integrals



7-187

CONFIGURATION 092

STEP 027

Stage ULF1 – Intermediate 1


�� ESP-2 with ORUs installed on Airlock forward trunnions.

�� The ORUs on the ESP-2 nadir side include the BDCU, FHRC, and UTA.

�� The ORU on the zenith side of the ESP-2 is the VSSA, which remains on the

ESP-2 until Stage 12A.1.

Element Properties: ISS Core Assembly - ULF1_INT1Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -10550 X = N/A N/A 799780 -196186 443728109371 Y = 290 Y = N/A N/A -196186 16600747 -64338




7-188




Element Properties: ESP-2 with ORUs (VSSA, BCDU, FHRC, UTA)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -516 X = -1708 -33631 4800 771 8662884 Y = 4993 Y = 2738 -1500 771 6618 258

Z = 6107 Z = 5639 -2734 866 258 8486Reference Point Description: Center of the port, aft trunnion pin



7-189



M. Falou/LM/281-333-6326 Stage ULF1 ISS – Intermediate 1 Produced By Contract Item Number


Total mass: 396331. lb 179773. kg Center of mass: X Y Z -32.68 .56 8.21 ft -9.96 .17 2.50 m Inertia tensor*: slug*ft**2 7865873. -106272. 2668524. -106272. 24592160. -110639. 2668524. -110639. 26080926. kg*m**2 10664687. -144086. 3618031. -144086. 33342476. -150006. 3618031. -150006. 35360972. Principal moments of inertia (IXX, IYY, IZZ): 7482281. 24583602. 26471261. slug*ft**2 10144921. 33331908. 35891308. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -3.84 -8.16 -.30 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.65E+00 -6.79E+00 CPy -3.57E+00 .00E+00 -7.40E+00 CPz -1.14E-01 -8.31E-01 .00E+00 X m Y m Z m CPx .00E+00 8.07E-01 -2.07E+00 CPy -1.09E+00 .00E+00 -2.25E+00 CPz -3.48E-02 -2.53E-01 .00E+00 Projected areas: X Y Z 4008.30 4160.88 11921.26 ft**2 372.38 386.56 1107.52 m**2 *Off-diagonal elements are negative integrals



7-190



M. Falou/LM/281-333-6326 Stage ULF1 Orbiter – Intermediate 1 Produced By Contract Item Number


Total mass: 237001. lb 107502. kg Center of mass: X Y Z 35.81 -.01 55.32 ft 10.91 .00 16.86 m Inertia tensor*: slug*ft**2 7836470. -540. 266386. -540. 7538230. -6061. 266386. -6061. 948828. kg*m**2 10624821. -732. 361171. -732. 10220463. -8217. 361171. -8217. 1286437. Principal moments of inertia (IXX, IYY, IZZ): 7846516. 7538001. 938506. slug*ft**2 10638772. 10220469. 1272482. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .05 2.21 .14 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.73E-02 -1.46E+00 CPy -3.86E+00 .00E+00 -1.41E+00 CPz -1.32E+00 1.67E-02 .00E+00 X m Y m Z m CPx .00E+00 5.27E-03 -4.46E-01 CPy -1.18E+00 .00E+00 -4.29E-01 CPz -4.04E-01 5.09E-03 .00E+00 Projected areas: X Y Z 4393.25 2148.22 740.27 ft**2 408.15 199.58 68.77 m**2 *Off-diagonal elements are negative integrals



7-191



M. Falou/LM/281-333-6326 Stage ULF1 Mated – Intermediate 1 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0030




7-192



M. Falou/LM/281-333-6326 Stage ULF1 Mated – Intermediate 1 Produced By Contract Item Number


Total mass: 633333. lb 287275. kg Center of mass: X Y Z -7.05 .35 25.84 ft -2.15 .11 7.88 m Inertia tensor*: slug*ft**2 25934270. 75938. -11938753. 75938. 63985168. 8999. -11938753. 8999. 48655696. kg*m**2 35162132. 102959. -16186768. 102959. 86752200. 12202. -16186768. 12202. 65968236. Principal moments of inertia (IXX, IYY, IZZ): 20813934. 63983354. 53773546. slug*ft**2 28220768. 86752432. 72909368. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .08 23.21 .11 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.34E+00 4.02E+00 CPy -5.89E+00 .00E+00 -6.85E+00 CPz -2.20E+01 -4.55E-01 .00E+00 X m Y m Z m CPx .00E+00 4.08E-01 1.23E+00 CPy -1.80E+00 .00E+00 -2.09E+00 CPz -6.71E+00 -1.39E-01 .00E+00 Projected areas: X Y Z 7284.27 6305.12 12547.65 ft**2 676.73 585.76 1165.72 m**2 *Off-diagonal elements are negative integrals



7-193

CONFIGURATION 109

STEP 028



�� The Shuttle RMS removes the fully loaded Raffaello MPLM from the Orbiter

payload bay and berths it to Unity Node 1 nadir CBM.

Element Properties: MPLM (loaded, berthed to Unity nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4527 X = -4463 -30876 34580 -95 -9988805 Y = 62 Y = -1 -2705 -95 39228 512

Z = 10088 Z = 6844 5 -998 512 26046Reference Point Description: Center of zenith MPLM CBM interface with Unity



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Total mass: 415744. lb 188578. kg Center of mass: X Y Z -31.85 .53 9.38 ft -9.71 .16 2.86 m Inertia tensor*: slug*ft**2 8247877. -98464. 2412609. -98464. 25160080. -99266. 2412609. -99266. 26283304. kg*m**2 11182614. -133500. 3271058. -133500. 34112472. -134587. 3271058. -134587. 35635360. Principal moments of inertia (IXX, IYY, IZZ): 7930056. 25151171. 26608184. slug*ft**2 10752041. 34101452. 36076956. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -4.43 -7.49 -.28 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.61E+00 -6.95E+00 CPy -3.23E+00 .00E+00 -6.72E+00 CPz -9.47E-01 -7.95E-01 .00E+00 X m Y m Z m CPx .00E+00 7.95E-01 -2.12E+00 CPy -9.86E-01 .00E+00 -2.05E+00 CPz -2.89E-01 -2.42E-01 .00E+00 Projected areas: X Y Z 4131.23 4404.11 11921.26 ft**2 383.80 409.16 1107.52 m**2 *Off-diagonal elements are negative integrals



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T. Farrell/EA4/281-483-8123 International Space Station Program 8pproved By Configuration 109 – Step 028





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CONFIGURATION 093

STEP 029



�� Prepare Raffaello MPLM for return to Orbiter payload bay.

�� Replace External Attached MISSE payloads 1A, on Airlock nadir HPGT 2, and

1B, on the starboard face of the crew lock, with External Attached MISSE

payloads 1C and 1D, respectively.

�� Install FPMU and stanchion on S1 truss outboard upper [port 2].

�� Install external camera and stanchion on P1 truss inboard lower [port 7].



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This page is included for formatting purposes.



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Total mass: 415744. lb 188578. kg Center of mass: X Y Z -31.85 .53 9.38 ft -9.71 .16 2.86 m Inertia tensor*: slug*ft**2 8247877. -98464. 2412609. -98464. 25160080. -99266. 2412609. -99266. 26283304. kg*m**2 11182614. -133500. 3271058. -133500. 34112472. -134587. 3271058. -134587. 35635360. Principal moments of inertia (IXX, IYY, IZZ): 7930056. 25151171. 26608184. slug*ft**2 10752041. 34101452. 36076956. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -4.43 -7.49 -.28 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.55E+00 -6.94E+00 CPy -3.23E+00 .00E+00 -6.72E+00 CPz -9.47E-01 -7.95E-01 .00E+00 X m Y m Z m CPx .00E+00 7.77E-01 -2.12E+00 CPy -9.86E-01 .00E+00 -2.05E+00 CPz -2.89E-01 -2.42E-01 .00E+00 Projected areas: X Y Z 4134.80 4404.11 11921.26 ft**2 384.14 409.16 1107.52 m**2 *Off-diagonal elements are negative integrals



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CONFIGURATION 094

STEP 030

Stage ULF1 – Before Separation


�� Shuttle RMS removes the Raffaello MPLM from Unity Node 1 nadir CBM and

returns it to the Orbiter payload bay.

Element Properties: MPLM (unloaded, berthed to Unity nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4527 X = -4463 -30876 34580 -95 -9988805 Y = 62 Y = -1 -2705 -95 39228 512

Z = 10088 Z = 6844 5 -998 512 26046Reference Point Description: Center of zenith MPLM CBM interface with Unity



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M. Falou/LM/281-333-6326 Stage ULF1 ISS – Before Separation Produced By Contract Item Number





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M. Falou/LM/281-333-6326 Stage ULF1 Orbiter – Before Separation Produced By Contract Item Number





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M. Falou/LM/281-333-6326 Stage ULF1 Mated – Before Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0033




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M. Falou/LM/281-333-6326 Stage ULF1 Mated – Before Separation Produced By Contract Item Number





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CONFIGURATION 095

STEP 031

Stage ULF1 – After Separation


�� ULF 1, flown on STS-114 Space Shuttle Atlantis [OV-104], delivered Raffaello

MPLM and two WVS stantions to outfit the ISS.

�� The ESP-2 with ORUs was installed on the airlock forward trunnion pins.

.



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M. Falou/LM/281-333-6326 Stage ULF1 ISS – After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0034




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M. Falou/LM/281-333-6326 Stage ULF1 ISS – After Separation Produced By Contract Item Number





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CONFIGURATION 096

STEP 032



�� Flight 10P [Progress M-47] vehicle undocked from Zvezda Service Module aft

docking port before 11P Progress launch.


loading waste.

�� Prior to this configuration, SSRMS is relocated from Destiny Lab module to MBS. Element Properties: ISS Core Assembly - 10P_ASMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -10480 X = N/A N/A 795527 -190097 440533108154 Y = 290 Y = N/A N/A -190097 16537904 -65095

Z = 3720 Z = N/A N/A 440533 -65095 16505049Reference Point Description: None SSRMS (on MT on P1)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 4780 X = N/A N/A 11880 1945 -3111502 Y = -9095 Y = N/A N/A 1945 2524 1302

Z = 637 Z = N/A N/A -311 1302 10489Reference Point Description: N/A



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CONFIGURATION 097

STEP 033



�� Flight 11P [Progress M1-10] vehicle launched and delivered to orbit by Soyuz

launch vehicle.

�� Eleventh Progress vehicle of ISS assembly sequence docked to Service Module



X = -39610 X = -35689 350 5189 33 -186934 Y = 7 Y = 4 0 33 32151 626




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Dean Coleman NAS9-19100 Science Engineering Analysis & Test 02-MP0065 NASA Center/Division Revision Date JSC/Systems Engineering Office Origional 5/1/02

Total mass: 393648. lb 178556. kg Center of mass: X Y Z -32.40 .33 7.97 ft -9.88 .10 2.43 m Inertia tensor*: slug*ft**2 7919655. 39899. 2752892. 39899. 24622612. -136148. 2752892. -136148. 26248424. kg*m**2 10737605. 54096. 3732419. 54096. 33383764. -184591. 3732419. -184591. 35588068. Principal moments of inertia (IXX, IYY, IZZ): 7514674. 24613905. 26660292. slug*ft**2 10188842. 33372994. 36147608. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -3.59 -8.36 .20 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.89E+00 -6.86E+00 CPy -3.95E+00 .00E+00 -7.70E+00 CPz -1.14E-01 -7.89E-01 .00E+00 X m Y m Z m CPx .00E+00 8.81E-01 -2.09E+00 CPy -1.20E+00 .00E+00 -2.35E+00 CPz -3.48E-02 -2.41E-01 .00E+00 Projected areas: X Y Z 3966.56 4128.23 11985.26 ft**2 368.51 383.52 1113.47 m**2 *Off-diagonal elements are negative integrals



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CONFIGURATION 098

STEP 034



�� Flight 11P [Progress M1-10] vehicle undocked from Zvezda Service Module aft



loading waste.


X = -10620 X = N/A N/A 798167 -193266 442893108902 Y = 290 Y = N/A N/A -193266 16574066 -64301




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Dean Coleman NAS9-19100 Science Engineering Analysis & Test 02-MP0066 NASA Center/Division Revision Date JSC/Systems Engineering Office A 5/1/02




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CONFIGURATION 099

STEP 035



�� Flight 12P [Progress M-48] vehicle launched and delivered to orbit by Soyuz

launch vehicle.

�� Twelveth Progress vehicle of ISS assembly sequence docked to Service Module



X = -39610 X = -35689 350 5189 33 -186934 Y = 7 Y = 4 0 33 32151 626




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Total mass: 395297. lb 179304. kg Center of mass: X Y Z -32.69 .33 7.98 ft -9.96 .10 2.43 m Inertia tensor*: slug*ft**2 7922539. 39743. 2769527. 39743. 24664566. -135696. 2769527. -135696. 26289132. kg*m**2 10741515. 53885. 3754973. 53885. 33440646. -183979. 3754973. -183979. 35643260. Principal moments of inertia (IXX, IYY, IZZ): 7513568. 24655922. 26704919. slug*ft**2 10187342. 33429964. 36208116. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -3.57 -8.39 .20 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 2.89E+00 -6.88E+00 CPy -3.66E+00 .00E+00 -7.72E+00 CPz 1.73E-01 -7.92E-01 .00E+00 X m Y m Z m CPx .00E+00 8.81E-01 -2.10E+00 CPy -1.12E+00 .00E+00 -2.35E+00 CPz 5.27E-02 -2.41E-01 .00E+00 Projected areas: X Y Z 3966.56 4128.23 11985.26 ft**2 368.51 383.52 1113.47 m**2 *Off-diagonal elements are negative integrals



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CONFIGURATION 110

STEP 036


(STS 115 on Space Shuttle Endeavour)

�� STS - 115 Space Shuttle Endeavour [OV-105] docked to PMA-2 tail nadir.

�� Stage 12A delivers ITS P3, ITS P4, WETA, a VSSA stanchion, 2A and 4A solar

arrays, and one PV radiator.


o MT relocated to worksite #7

o P6 solar arrays are fixed at 150/210 (2B/4B) degrees.





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Total mass: 395297. lb 179304. kg Center of mass: X Y Z -32.69 -.59 7.98 ft -9.96 -.18 2.43 m Inertia tensor*: slug*ft**2 8781555. 533316. 2763210. 533316. 24664172. -219252. 2763210. -219252. 27141072. kg*m**2 11906184. 723079. 3746408. 723079. 33440112. -297266. 3746408. -297266. 36798336. Principal moments of inertia (IXX, IYY, IZZ): 8355234. 24675864. 27553825. slug*ft**2 11328522. 33457002. 37359112. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -2.49 -8.39 1.99 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.79E+00 -2.70E+01 CPy -3.62E+00 .00E+00 -7.98E+00 CPz -6.37E-01 -7.50E-01 .00E+00 X m Y m Z m CPx .00E+00 5.44E-01 -8.24E+00 CPy -1.10E+00 .00E+00 -2.43E+00 CPz -1.94E-01 -2.29E-01 .00E+00 Projected areas: X Y Z 7158.45 4150.78 11346.49 ft**2 665.04 385.62 1054.12 m**2 *Off-diagonal elements are negative integrals



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Total mass: 250305. lb 113537. kg Center of mass: X Y Z 35.59 -.08 53.68 ft 10.85 -.02 16.36 m Inertia tensor*: slug*ft**2 8950818. -25290. 196855. -25290. 8589344. -39038. 196855. -39038. 1028367. kg*m**2 12135674. -34288. 266899. -34288. 11645582. -52929. 266899. -52929. 1394278. Principal moments of inertia (IXX, IYY, IZZ): 8957300. 8587400. 1023252. slug*ft**2 12144840. 11643307. 1387387. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .19 1.44 4.08 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 8.24E-02 1.76E-01 CPy -3.67E+00 .00E+00 -4.97E-01 CPz -1.10E+00 8.18E-02 .00E+00 X m Y m Z m CPx .00E+00 2.51E-02 5.37E-02 CPy -1.12E+00 .00E+00 -1.51E-01 CPz -3.35E-01 2.49E-02 .00E+00 Projected areas: X Y Z 4393.25 2201.95 740.27 ft**2 408.15 204.57 68.77 m**2 *Off-diagonal elements are negative integrals



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Total mass: 645603. lb 292841. kg Center of mass: X Y Z -6.22 -.39 25.70 ft -1.90 -.12 7.83 m Inertia tensor*: slug*ft**2 27681948. 341928. -11902499. 341928. 65406156. -369470. -11902499. -369470. 50374992. kg*m**2 37531664. 463592. -16137615. 463592. 88678800. -500933. -16137615. -500933. 68299288. Principal moments of inertia (IXX, IYY, IZZ): 22582862. 65427380. 55448398. slug*ft**2 30619186. 88710328. 75180232. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 2.63 23.18 .25 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 9.39E-01 -1.83E+01 CPy -6.43E+00 .00E+00 -7.16E+00 CPz -2.30E+01 -1.01E+00 .00E+00 X m Y m Z m CPx .00E+00 2.86E-01 -5.59E+00 CPy -1.96E+00 .00E+00 -2.18E+00 CPz -7.02E+00 -3.08E-01 .00E+00 Projected areas: X Y Z 10496.26 6317.64 12065.37 ft**2 975.13 586.93 1120.91 m**2 *Off-diagonal elements are negative integrals



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CONFIGURATION 111

STEP 037



�� Space Station RMS removes the ITS P3/ITS P4 structure from the Orbiter

payload bay and installs it onto the port interface of ITS P1.



7-238

CONFIGURATION 111

STEP 037



Element Properties: P3/P4 Truss Assembly (stowed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 297 X = 0 -35339 1139460 6847 -82615739 Y = -25436 Y = -23000 6621 6847 27691 -3126

Z = -8 Z = -2482 23004 -826 -3126 1137710Reference Point Description: Center of P3 starboard, zenith trunnion pin



7-239





Total mass: 429996. lb 195043. kg Center of mass: X Y Z -29.97 -7.28 7.32 ft -9.14 -2.22 2.23 m Inertia tensor*: slug*ft**2 16496572. 3303732. 3037789. 3303732. 25875412. -898959. 3037789. -898959. 35910800. kg*m**2 22366338. 4479258. 4118687. 4479258. 35082332. -1218824. 4118687. -1218824. 48688484. Principal moments of inertia (IXX, IYY, IZZ): 14970098. 26921101. 36389157. slug*ft**2 20297348. 36501228. 49338580. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .36 -8.60 17.54 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 3.18E+00 -2.53E+01 CPy -6.32E+00 .00E+00 -7.32E+00 CPz -2.58E+00 3.96E+00 .00E+00 X m Y m Z m CPx .00E+00 9.69E-01 -7.71E+00 CPy -1.93E+00 .00E+00 -2.23E+00 CPz -7.85E-01 1.21E+00 .00E+00 Projected areas: X Y Z 7608.71 4152.64 11597.57 ft**2 706.87 385.79 1077.45 m**2 *Off-diagonal elements are negative integrals



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Total mass: 645603. lb 292841. kg Center of mass: X Y Z -7.96 -4.86 23.47 ft -2.43 -1.48 7.15 m Inertia tensor*: slug*ft**2 35087056. 1153590. -10954830. 1153590. 63259352. -2497391. -10954830. -2497391. 56538424. kg*m**2 47571640. 1564057. -14852749. 1564057. 85768128. -3386005. -14852749. -3386005. 76655776. Principal moments of inertia (IXX, IYY, IZZ): 30480219. 65145569. 59254238. slug*ft**2 41326892. 88328232. 80340416. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 34.41 22.79 .18 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 1.78E+00 -1.64E+01 CPy -5.59E+00 .00E+00 -5.49E+00 CPz -2.06E+01 1.58E+00 .00E+00 X m Y m Z m CPx .00E+00 5.41E-01 -5.01E+00 CPy -1.70E+00 .00E+00 -1.67E+00 CPz -6.29E+00 4.82E-01 .00E+00 Projected areas: X Y Z 10943.46 6188.72 12320.23 ft**2 1016.68 574.95 1144.59 m**2 *Off-diagonal elements are negative integrals



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CONFIGURATION 112

STEP 038



�� Rotate P4 truss keel pin.

�� Remove and stow P3 truss keel pin.

�� Remove SARJ locks to allow rotation of the alpha gimbal joint.

�� Rotate SARJ 180 degrees to zero degrees position [launch and install position

is 180 degrees].

�� Deploy channels 4A and 2A solar arrays.

�� Relocate the SASA from P6 zenith to P1

�� Relocate the BSP and transponder from Z1 to P1.

�� Deploy P4 truss PV radiator.

�� Install the WETA and stanchion on P3 truss [port 10], One stanchion remains

in VSSA on ESP-2.

�� Relocate MT to worksite #4.

�� Lock the ITS P3 truss SARJ.

�� P6 solar arrays are fixed at 150/210 (2B/4B) degrees

�� P4 solar arrays are fixed at 90/270 (2A/4A) degrees.



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CONFIGURATION 112

STEP 038



Element Properties: P3/P4 Truss Assembly (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 182 X = 0 -35339 184198 -2811 148713627 Y = -28364 Y = -23000 6621 -2811 51160 -10673

Z = 258 Z = -2482 23004 1487 -10673 154444Reference Point Description: Center of P3 starboard, zenith trunnion pin



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CONFIGURATION 112

STEP 038



P4 Radiator (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -380 X = N/A N/A 14427 -4 150731 Y = -29402 Y = N/A N/A -4 13702 195


P4 PIF Solar ArrayMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 13252 X = 1096 -36435 8911 16 -16961074 Y = -33417 Y = -33420 3593 16 174208 1

Z = 705 Z = 546 33424 -1696 1 182896Reference Point Description: Center of PV mast canister interface with beta gimbal

P4 PIA Solar ArrayMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -13966 X = -1810 -33529 8911 16 16961074 Y = -33420 Y = -33420 4914 16 174208 -1

Z = -616 Z = -775 33424 1696 -1 182896Reference Point Description: Center of PV mast canister interface with beta gimbal

S-Band Antenna at P1Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 174 X = N/A N/A 17 1 2103 Y = -9062 Y = N/A N/A 1 18 -5




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Total mass: 430075. lb 195079. kg Center of mass: X Y Z -30.01 -6.81 7.42 ft -9.15 -2.07 2.26 m Inertia tensor*: slug*ft**2 17256852. 2847914. 2983567. 2847914. 26377340. -772696. 2983567. -772696. 37196620. kg*m**2 23397138. 3861251. 4045172. 3861251. 35762856. -1047634. 4045172. -1047634. 50431824. Principal moments of inertia (IXX, IYY, IZZ): 15992437. 27192153. 37643726. slug*ft**2 21683496. 36868736. 51039600. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .42 -8.27 15.93 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.09E+00 -2.26E+01 CPy -6.20E+00 .00E+00 -7.25E+00 CPz 8.36E+00 -3.21E+01 .00E+00 X m Y m Z m CPx .00E+00 -9.41E-01 -6.90E+00 CPy -1.89E+00 .00E+00 -2.21E+00 CPz 2.55E+00 -9.79E+00 .00E+00 Projected areas: X Y Z 8119.80 4193.62 17719.28 ft**2 754.35 389.60 1646.18 m**2 *Off-diagonal elements are negative integrals



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Total mass: 644227. lb 292217. kg Center of mass: X Y Z -8.10 -4.56 23.48 ft -2.47 -1.39 7.16 m Inertia tensor*: slug*ft**2 35748536. 840511. -10934336. 840511. 63606296. -2264167. -10934336. -2264167. 57705324. kg*m**2 48468484. 1139579. -14824962. 1139579. 86238520. -3069797. -14824962. -3069797. 78237880. Principal moments of inertia (IXX, IYY, IZZ): 31231052. 65422961. 60401278. slug*ft**2 42344916. 88704336. 81895640. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 37.06 22.45 -.17 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -2.68E+00 -1.56E+01 CPy -5.80E+00 .00E+00 -5.92E+00 CPz -1.15E+01 -3.30E+01 .00E+00 X m Y m Z m CPx .00E+00 -8.18E-01 -4.75E+00 CPy -1.77E+00 .00E+00 -1.80E+00 CPz -3.50E+00 -1.01E+01 .00E+00 Projected areas: X Y Z 11452.95 6324.61 18369.99 ft**2 1064.01 587.58 1706.63 m**2 *Off-diagonal elements are negative integrals



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CONFIGURATION 113

STEP 039


(STS 115 on Space Shuttle Endeabour)

�� STS-115 Space Shuttle Endeavour [OV-105] undocked from ISS.

�� Stage 12A delivered ITS P3 and ITS P4 to the ISS.

�� Stage 12A delivered the 1A and 3A Solar Arrays located on the P4 truss

segment. The solar arrays are deployed to provide power to the ISS

�� Stage 12A delivered the P4 truss PV radiator.



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CONFIGURATION 114

STEP 040

Flight 6S – After Rendezvous


�� Flight 6S [Soyuz TMA-2] vehicle docked to Zarya FGB nadir docking port.

Soyuz vehicle Solar Arrays clocked 45 degrees.

�� 6S Soyuz will maintain crew return capability previously assured by 5S Soyuz

vehicle.

Element Properties: 6S Soyuz (docked to FGB nadir)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -11136 X = -11118 -24221 23811 443 06745 Y = 3 Y = 4 -1140 443 23811 0




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M. Falou/LM/281-333-6326 Flight 6S ISS – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0043




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M. Falou/LM/281-333-6326 Flight 6S ISS – After Rendezvous Produced By Contract Item Number





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CONFIGURATION 115

STEP 041

Flight 5S – After Separation


�� Flight 5S [Soyuz TMA-1] vehicle undocked from Pirs DC 1 nadir docking port.

�� 6S Soyuz remains docked to Zarya FGB nadir docking port maintaining crew

return capability previously assured by 5S Soyuz vehicle.



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M. Falou/LM/281-333-6326 Flight 5S ISS – After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0044




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M. Falou/LM/281-333-6326 Flight 5S ISS – After Separation Produced By Contract Item Number


Total mass: 430075. lb 195079. kg Center of mass: X Y Z -28.58 -6.81 6.96 ft -8.71 -2.07 2.12 m Inertia tensor*: slug*ft**2 16884952. 2718393. 2234305. 2718393. 24943678. -731097. 2234305. -731097. 36134180. kg*m**2 22892912. 3685644. 3029309. 3685644. 33819072. -991234. 3029309. -991234. 48991348. Principal moments of inertia (IXX, IYY, IZZ): 15781775. 25773926. 36404698. slug*ft**2 21397868. 34945820. 49359652. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -.24 -6.59 17.03 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.07E+00 -2.31E+01 CPy -5.52E+00 .00E+00 -6.70E+00 CPz 6.94E+00 -3.21E+01 .00E+00 X m Y m Z m CPx .00E+00 -9.36E-01 -7.03E+00 CPy -1.68E+00 .00E+00 -2.04E+00 CPz 2.11E+00 -9.78E+00 .00E+00 Projected areas: X Y Z 7984.75 4337.30 17729.10 ft**2 741.81 402.95 1647.09 m**2 *Off-diagonal elements are negative integrals



7-263


Stage 12A.1 – After Rendezvous


�� STS-116 Space Shuttle Atlantis [OV-104] docked to PMA 2 tail nadir.

�� Stage 12A.1 delivers ITS port 5 (P5) truss, PVRGF OSE, pump module, DDCU

Cold Plate and MBSU Cold Plate to ISS.


o MT was relocated to worksite #5

o P6 beta gimbals were fixed 150/210 (2B/4B) degrees.

o P port SARJ fixed at 0 degrees, P4 solar arrays fixed at 90/270 (2A/4A)

degrees port SARJ fixed at 0 degrees, P4 solar arrays fixed at 90/270

(2A/4A) degrees.





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M. Falou/LM/281-333-6326 Stage 12A.1 ISS – After Rendezvous Produced By Contract Item Number


Total mass: 430075. lb 195079. kg Center of mass: X Y Z -28.58 -7.42 6.96 ft -8.71 -2.26 2.12 m Inertia tensor*: slug*ft**2 16867004. 3040475. 2234305. 3040475. 24943678. -783054. 2234305. -783054. 36116232. kg*m**2 22868576. 4122329. 3029309. 4122329. 33819072. -1061678. 3029309. -1061678. 48967012. Principal moments of inertia (IXX, IYY, IZZ): 15577037. 25959394. 36388074. slug*ft**2 21120272. 35197288. 49337112. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -.18 -6.57 18.51 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -2.46E+00 -2.30E+01 CPy -5.52E+00 .00E+00 -6.70E+00 CPz 7.04E+00 -3.16E+01 .00E+00 X m Y m Z m CPx .00E+00 -7.51E-01 -7.03E+00 CPy -1.68E+00 .00E+00 -2.04E+00 CPz 2.14E+00 -9.64E+00 .00E+00 Projected areas: X Y Z 7988.23 4337.30 17776.65 ft**2 742.13 402.95 1651.50 m**2 *Off-diagonal elements are negative integrals



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M. Falou/LM/281-333-6326 Stage 12A.1 Orbiter – After Rendezvous Produced By Contract Item Number





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M. Falou/LM/281-333-6326 Stage 12A.1 Mated – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0045




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M. Falou/LM/281-333-6326 Stage 12A.1 Mated – After Rendezvous Produced By Contract Item Number


Total mass: 665962. lb 302075. kg Center of mass: X Y Z -5.79 -4.81 24.00 ft -1.76 -1.47 7.32 m Inertia tensor*: slug*ft**2 36048516. 793629. -12183181. 793629. 63188652. -2470332. -12183181. -2470332. 56934724. kg*m**2 48875204. 1076016. -16518168. 1076016. 85672272. -3349319. -16518168. -3349319. 77193088. Principal moments of inertia (IXX, IYY, IZZ): 30441260. 65459301. 60266497. slug*ft**2 41274068. 88753608. 81712896. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 41.64 24.74 -.60 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -2.44E+00 -1.61E+01 CPy -7.01E+00 .00E+00 -6.30E+00 CPz -1.37E+01 -3.29E+01 .00E+00 X m Y m Z m CPx .00E+00 -7.42E-01 -4.91E+00 CPy -2.14E+00 .00E+00 -1.92E+00 CPz -4.18E+00 -1.00E+01 .00E+00 Projected areas: X Y Z 11457.07 6439.60 18427.36 ft**2 1064.40 598.26 1711.96 m**2 *Off-diagonal elements are negative integrals



7-269

CONFIGURATION 117

STEP 043

Stage 12A.1 – Intermediate 1



�� Space Station RMS attaches the ITS Port 5 (P5) truss to P4 truss port

interface.



7-270

CONFIGURATION 117

STEP 043



Element Properties: P5 TrussMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -486 X = -3215 -32124 5135 -191 301982 Y = -34409 Y = -35324 4139 -191 4806 1

Z = 20 Z = 0 35328 30 1 3033Reference Point Description: Center of keel pin



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M. Falou/LM/281-333-6326 Stage 12A.1 ISS – Intermediate 1 Produced By Contract Item Number


Total mass: 434676. lb 197166. kg Center of mass: X Y Z -28.30 -9.76 6.89 ft -8.62 -2.97 2.10 m Inertia tensor*: slug*ft**2 19680696. 4092760. 2260871. 4092760. 25058738. -989856. 2260871. -989856. 39026400. kg*m**2 26683430. 5549036. 3065328. 5549036. 33975072. -1342064. 3065328. -1342064. 52912672. Principal moments of inertia (IXX, IYY, IZZ): 17194892. 27262659. 39305692. slug*ft**2 23313856. 36964332. 53292992. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .94 -6.43 28.22 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -8.20E-01 -2.29E+01 CPy -5.78E+00 .00E+00 -6.63E+00 CPz 6.75E+00 -2.98E+01 .00E+00 X m Y m Z m CPx .00E+00 -2.50E-01 -6.97E+00 CPy -1.76E+00 .00E+00 -2.02E+00 CPz 2.06E+00 -9.07E+00 .00E+00 Projected areas: X Y Z 8045.02 4341.60 17788.28 ft**2 747.41 403.35 1652.59 m**2 *Off-diagonal elements are negative integrals



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M. Falou/LM/281-333-6326 Stage 12A.1 Orbiter – Intermediate 1 Produced By Contract Item Number





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M. Falou/LM/281-333-6326 Stage 12A.1 Mated – Intermediate 1 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0046




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M. Falou/LM/281-333-6326 Stage 12A.1 Mated – Intermediate 1 Produced By Contract Item Number


Total mass: 665687. lb 301951. kg Center of mass: X Y Z -6.04 -6.39 23.62 ft -1.84 -1.95 7.20 m Inertia tensor*: slug*ft**2 38982940. 1171797. -11995130. 1171797. 62913320. -3193608. -11995130. -3193608. 59698244. kg*m**2 52853748. 1588743. -16263205. 1588743. 85298968. -4329949. -16263205. -4329949. 80939912. Principal moments of inertia (IXX, IYY, IZZ): 33489006. 60473551. 67626935. slug*ft**2 45406384. 81993632. 91692616. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -35.50 24.65 -.57 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -1.37E+00 -1.58E+01 CPy -6.86E+00 .00E+00 -6.03E+00 CPz -1.35E+01 -3.17E+01 .00E+00 X m Y m Z m CPx .00E+00 -4.17E-01 -4.81E+00 CPy -2.09E+00 .00E+00 -1.84E+00 CPz -4.10E+00 -9.67E+00 .00E+00 Projected areas: X Y Z 11514.62 6427.75 18438.99 ft**2 1069.74 597.16 1713.04 m**2 *Off-diagonal elements are negative integrals



7-275

CONFIGURATION 118

STEP 044

Stage 12A.1 – Before Separation


�� Space Station RMS relocates the PVRGF OSE from ITS P5 to the MBS LEE.

�� Connect P4 truss Channel 4B Solar Array power to the ISS MBSU and activate

first EATCS loop.

�� Deactivate and retract P6 POA port Solar Array.

�� Unlock P4 truss SARJ.

�� Transfer the Pump Module, DDCU cold plate and MBSU cold plate to the ESP 2

from the ICC in the orbiter payload bay.

�� Transfer VSSA FSE from the ESP 2 to the ICC.

�� Transfer the PFCS from ESP 1 to the ICC.

�� Connect P4 truss Channel 2A power to ISS MBSU and activate second EATCS

loop.

�� Relocate MT to worksite #4

�� CETA cart configuration is CETA B-CETA A-MT.

�� P6 beta gimbals fixed at 150/210 (2B/4B) degrees.

�� Port SARJ fixed at 90 degrees, P4 beta gimbals fixed at 290/70 (2A/4A)degrees.



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CONFIGURATION 118

STEP 044


(STS-116 Space Shuttle Atlantis) Element Properties: P6 POA Retracted Solar Array (port)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -5183 X = -5200 -30139 1806 -66 -18531062 Y = -2954 Y = -1450 18019 -66 4633 111

Z = -13791 Z = -13880 1444 -1853 111 3948Reference Point Description: Center of PV mast canister interface with beta gimbal



7-277

CONFIGURATION 118

STEP 044



Element Properties: MDM Radiator (on PMA 1 zenith)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]


Z = N/A Z = 3105 -250 N/A N/A N/AReference Point Description: Forward, starboard, zenith corner of the MDM radiator



7-278

CONFIGURATION 118

STEP 044



Element Properties: PVRGF (relocated to MBS LEE)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 4356 X = 4783 -40122 26 8 1105 Y = -852 Y = -1009 4597 8 32 -7

Z = -129 Z = -458 1013 1 -7 29Reference Point Description: Forward Grapple Fixture pin base



7-279

CONFIGURATION 118

STEP 044



Element Properties: EATCS Radiator with support structure (deployed on S1 in zero position)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -2684 X = -50 -35289 54183 -280 415095 Y = 14717 Y = 14692 4141 -280 183707 47

Z = -6 Z = -2 -14688 41 47 141401Reference Point Description: Center of the thermal radiator rotary joint

EATCS Radiator with support structure (deployed on P1 in zero position)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -2684 X = -50 -35289 54183 280 -415095 Y = -14717 Y = -14692 4137 280 183707 47

Z = 6 Z = 2 14696 -41 47 141401Reference Point Description: Center of the thermal radiator rotary joint



7-280




7-281



M. Falou/LM/281-333-6326 Stage 12A.1 ISS – Before Separation Produced By Contract Item Number


Total mass: 435926. lb 197733. kg Center of mass: X Y Z -28.29 -7.58 6.77 ft -8.62 -2.31 2.06 m Inertia tensor*: slug*ft**2 18756882. 2974897. 2337543. 2974897. 25287020. -757461. 2337543. -757461. 37008892. kg*m**2 25430906. 4033417. 3169281. 4033417. 34284580. -1026979. 3169281. -1026979. 50177300. Principal moments of inertia (IXX, IYY, IZZ): 17298915. 26436535. 37314837. slug*ft**2 23454896. 35844224. 50593672. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .71 -7.10 21.06 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.94E+01 -1.30E+01 CPy 2.32E+00 .00E+00 -6.29E+00 CPz -5.91E+00 1.71E+01 .00E+00 X m Y m Z m CPx .00E+00 -1.20E+01 -3.96E+00 CPy 7.08E-01 .00E+00 -1.92E+00 CPz -1.80E+00 5.21E+00 .00E+00 Projected areas: X Y Z 12480.01 6895.22 8473.72 ft**2 1159.43 640.59 787.23 m**2 *Off-diagonal elements are negative integrals



7-282



M. Falou/LM/281-333-6326 Stage 12A.1 Orbiter – Before Separation Produced By Contract Item Number





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M. Falou/LM/281-333-6326 Stage 12A.1 Mated – Before Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0047




7-284



M. Falou/LM/281-333-6326 Stage 12A.1 Mated – Before Separation Produced By Contract Item Number


Total mass: 664188. lb 301270. kg Center of mass: X Y Z -6.25 -4.98 23.37 ft -1.90 -1.52 7.12 m Inertia tensor*: slug*ft**2 37825180. 722191. -11847516. 722191. 62943888. -2459667. -11847516. -2459667. 57356748. kg*m**2 51284036. 979159. -16063068. 979159. 85340416. -3334860. -16063068. -3334860. 77765272. Principal moments of inertia (IXX, IYY, IZZ): 32231189. 60412435. 65477291. slug*ft**2 43700960. 81910768. 88778000. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -44.67 25.31 -.82 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.19E+01 -1.43E+01 CPy -6.14E+00 .00E+00 -1.19E+01 CPz -2.26E+01 1.38E+01 .00E+00 X m Y m Z m CPx .00E+00 -9.73E+00 -4.35E+00 CPy -1.87E+00 .00E+00 -3.62E+00 CPz -6.90E+00 4.21E+00 .00E+00 Projected areas: X Y Z 15904.95 8999.66 9165.00 ft**2 1477.62 836.10 851.46 m**2 *Off-diagonal elements are negative integrals



7-285

CONFIGURATION 119

STEP 045

Stage 12A.1 – After Separation


�� STS – 117 Space Shuttle Atlantis [OV-104] undocked from ISS.

�� Stage 12A.1 delivered ITS P5.

�� S1 and P1 EATCS radiators were activated for solar anti-tracking.

�� PVRGF OSE was relocated from P5 to the MBS LEE.

�� P6 truss Channel 4B Solar Array [port array] was deactivated and retracted.

�� The Pump Module, DDCU Cold Plate, and MBSU Cold Plate were transferred to

the ESP 2.

�� The VSSA FSE was transferred from the ESP 2 to the ICC.

�� The PFCS was transferred from ESP 1 to the ICC.



7-286




7-287



M. Falou/LM/281-333-6326 Stage 12A.1 ISS – After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0048




7-288



M. Falou/LM/281-333-6326 Stage 12A.1 ISS – After Separation Produced By Contract Item Number





7-289

CONFIGURATION 120

STEP 046



�� Flight 12P [Progress M-48] vehicle undocked from Zvezda Service Module aft



loading waste.


X = -10480 X = N/A N/A 781009 -168008 411222106574 Y = 290 Y = N/A N/A -168008 16613740 -66108




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7-291







7-292





Total mass: 415727. lb 188571. kg Center of mass: X Y Z -24.19 -7.96 6.45 ft -7.37 -2.42 1.97 m Inertia tensor*: slug*ft**2 18679638. 2551786. 1964099. 2551786. 19961386. -725200. 1964099. -725200. 31672004. kg*m**2 25326176. 3459756. 2662960. 3459756. 27063994. -983239. 2662960. -983239. 42941452. Principal moments of inertia (IXX, IYY, IZZ): 16426703. 21912414. 31971737. slug*ft**2 22272300. 29710152. 43349180. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 3.49 -7.49 37.08 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.90E+01 -1.27E+01 CPy 2.30E+00 .00E+00 -7.45E+00 CPz -7.16E+00 1.79E+01 .00E+00 X m Y m Z m CPx .00E+00 -1.19E+01 -3.86E+00 CPy 7.00E-01 .00E+00 -2.27E+00 CPz -2.18E+00 5.47E+00 .00E+00 Projected areas: X Y Z 12479.77 6725.36 8297.57 ft**2 1159.41 624.81 770.87 m**2 *Off-diagonal elements are negative integrals



7-293

CONFIGURATION 121

STEP 047



�� Flight 13P [Progress M1-49] vehicle launched and delivered to orbit by Soyuz

launch vehicle.

�� Thirteenth Progress vehicle of ISS assembly sequence docked to Zveda Service

Module aft docking port with Solar Arrays clocked 45 degrees.


o Retract and stow P6 starboard and aft EEATCS radiators.

o Transfer PVRGF from MBS LEE to P6 aft EEATCS radiator.

o Install Node 1 starboard CETA light.





7-294

CONFIGURATION 121

STEP 047



Element Properties: P6 Assembly (with aft and starboard EATCS radiators retracted)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4298 X = -4539 -30799 177891 -264 232914581 Y = 129 Y = -2496 7489 -264 211193 -6568

Z = -8400 Z = -3349 2501 2329 -6568 53462Reference Point Description: Center of port, nadir keel pin



7-295

CONFIGURATION 121

STEP 047




X = -39610 X = -35689 350 5189 33 -186934 Y = 7 Y = 4 0 33 32151 626


PVRGF OSE (relocated to P6 aft radiator)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -6718 X = -6919 -28420 41 0 0105 Y = 36 Y = 561 9665 0 17 0

Z = -5527 Z = -5526 -557 0 0 29Reference Point Description: Port Grapple Fixture pin base



7-296




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M. Falou/LM/281-333-6326 Stage 13P ISS – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0050




7-298



M. Falou/LM/281-333-6326 Stage 13P ISS – After Rendezvous Produced By Contract Item Number





7-299

CONFIGURATION 122

STEP 048


(STS – 117 Space Shuttle Endeavour)

�� STS-117 Space Shuttle Endeavour [OV-105] docked to PMA 2 tail nadir.

�� Stage 13A delivers ITS S3 and ITS S4, and 1A and 3A solar arrays.



o Port SARJ is fixed at 90 degrees and P4 beta gimbals are fixed at

290/70 (2A/4A) degrees.





7-300




7-301





Total mass: 431014. lb 195505. kg Center of mass: X Y Z -27.93 -6.68 6.70 ft -8.51 -2.04 2.04 m Inertia tensor*: slug*ft**2 19720744. 2418362. 2320594. 2418362. 25118168. -609804. 2320594. -609804. 37812984. kg*m**2 26737728. 3278858. 3146302. 3278858. 34055648. -826783. 3146302. -826783. 51267500. Principal moments of inertia (IXX, IYY, IZZ): 18500387. 26037036. 38111922. slug*ft**2 25083924. 35302560. 51674408. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 1.19 -7.04 20.69 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -4.20E+01 -1.28E+01 CPy 3.20E+00 .00E+00 -4.92E+00 CPz -5.95E+00 1.69E+01 .00E+00 X m Y m Z m CPx .00E+00 -1.28E+01 -3.89E+00 CPy 9.74E-01 .00E+00 -1.50E+00 CPz -1.81E+00 5.14E+00 .00E+00 Projected areas: X Y Z 12150.35 6442.03 8533.63 ft**2 1128.80 598.48 792.80 m**2 *Off-diagonal elements are negative integrals



7-302








7-303







7-304





Total mass: 680477. lb 308659. kg Center of mass: X Y Z -4.64 -4.25 24.44 ft -1.41 -1.29 7.45 m Inertia tensor*: slug*ft**2 39523192. 319506. -12556578. 319506. 64154128. -2230445. -12556578. -2230445. 58870224. kg*m**2 53586228. 433191. -17024426. 433191. 86981280. -3024076. -17024426. -3024076. 79817272. Principal moments of inertia (IXX, IYY, IZZ): 33329108. 62420425. 66792979. slug*ft**2 45189584. 84633320. 90561888. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -38.57 26.28 -1.45 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.38E+01 -1.49E+01 CPy -5.60E+00 .00E+00 -1.10E+01 CPz -2.40E+01 1.37E+01 .00E+00 X m Y m Z m CPx .00E+00 -1.03E+01 -4.54E+00 CPy -1.71E+00 .00E+00 -3.36E+00 CPz -7.31E+00 4.17E+00 .00E+00 Projected areas: X Y Z 15574.35 8661.76 9224.55 ft**2 1446.90 804.70 856.99 m**2 *Off-diagonal elements are negative integrals



7-305

CONFIGURATION 123

STEP 049



�� The Space Station RMS berths the ITS S3 and S4 structure to the starboard

interface of ITS S1 truss.



7-306

CONFIGURATION 123

STEP 049



Element Properties: S3/S4 Truss Assembly (stowed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 286 X = 0 -35339 189676 -1856 83915357 Y = 28548 Y = 22975 6621 -1856 27153 1824

Z = -23 Z = -2482 -22971 839 1824 187990Reference Point Description: Center of S3 port, zenith trunnion pin



7-307





Total mass: 464869. lb 210861. kg Center of mass: X Y Z -25.82 .62 6.20 ft -7.87 .19 1.89 m Inertia tensor*: slug*ft**2 29728890. -408683. 2511869. -408683. 25995706. 54359. 2511869. 54359. 48587948. kg*m**2 40306944. -554099. 3405635. -554099. 35245428. 73701. 3405635. 73701. 65876384. Principal moments of inertia (IXX, IYY, IZZ): 29448369. 25945687. 48915264. slug*ft**2 39927848. 35178704. 66322220. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .89 -7.40 6.87 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -4.41E+01 -1.20E+01 CPy 1.10E+00 .00E+00 -4.43E+00 CPz -7.61E+00 1.05E+01 .00E+00 X m Y m Z m CPx .00E+00 -1.34E+01 -3.67E+00 CPy 3.35E-01 .00E+00 -1.35E+00 CPz -2.32E+00 3.19E+00 .00E+00 Projected areas: X Y Z 12643.07 6443.55 8630.74 ft**2 1174.58 598.63 801.82 m**2 *Off-diagonal elements are negative integrals



7-308








7-309







7-310





Total mass: 680476. lb 308659. kg Center of mass: X Y Z -6.25 .41 21.88 ft -1.91 .13 6.67 m Inertia tensor*: slug*ft**2 48856780. -241979. -11243757. -241979. 62221908. 168728. -11243757. 168728. 67058480. kg*m**2 66240872. -328079. -15244481. -328079. 84361544. 228764. -15244481. 228764. 90919048. Principal moments of inertia (IXX, IYY, IZZ): 43489760. 62214675. 72427221. slug*ft**2 58966000. 84354352. 98201128. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 1.65 25.50 -.49 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.46E+01 -1.26E+01 CPy -4.62E+00 .00E+00 -8.96E+00 CPz -2.20E+01 9.94E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.06E+01 -3.85E+00 CPy -1.41E+00 .00E+00 -2.73E+00 CPz -6.70E+00 3.03E+00 .00E+00 Projected areas: X Y Z 16067.06 8528.32 9328.62 ft**2 1492.68 792.31 866.66 m**2 *Off-diagonal elements are negative integrals



7-311

CONFIGURATION 124

STEP 050


(STS - 117 Space Shuttle Endeavor)

�� Rotate S4 truss keel pin.

�� Relocate P6 truss EEATCS starboard radiator to S4 truss using the PVRFG

and the Space Station RMS.

�� Remove and stow S3 truss keel pin.

�� Move PVRGF OSE from S4 truss radiator to MBS LEE.

�� Deploy S4 truss radiator.

�� Retract P6 truss starboard Solar Array.

�� Unlock the S4 truss SARJ.


�� CETA Cart A is relocated to the starboard side of the MT.

�� Deploy and activate channels 1A and 3A solar arrays and connect them to the

MBSU.

�� Port SARJ is fixed at 90 degrees. P4 beta gimbals are fixed at 290/70 (2A/4A)

degrees,

�� Starboard SARJ is fixed at 270 degrees, and S4 beta gimbals are fixed at

300/60 (1A/3A) degrees.



7-312

CONFIGURATION 124

STEP 050



Element Properties: S3/S4 Truss Assembly (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -227 X = 0 -35339 162896 -11902 -40813952 Y = 28245 Y = 22975 6621 -11902 53543 2175

Z = 257 Z = -2482 -22971 -408 2175 199549Reference Point Description: Center of S3 port, zenith trunnion pin



7-313

CONFIGURATION 124

STEP 050



Element Properties: P6 POF Retracted Solar Array (starboard)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -3866 X = -3879 -31460 1803 63 -18491059 Y = 2964 Y = 1460 5527 63 4620 -113

Z = -13793 Z = -13880 -1462 -1849 -113 3935Reference Point Description: Center of PV mast canister interface with beta gimbal

S4 Solar Array (forward)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 621 X = 1814 -37153 180725 3762 14611074 Y = 33369 Y = 33390 4914 3762 176380 862

Z = 13966 Z = -775 -33386 1461 862 8911Reference Point Description: Center of PV mast canister interface with beta gimbal

S4 Solar Array (aft)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -699 X = -1100 -34239 180724 3762 -14771074 Y = 33367 Y = 33390 3593 3762 176381 -835

Z = -13252 Z = 546 -33386 -1477 -835 8911Reference Point Description: Center of PV mast canister interface with beta gimbal

S4 Radiator (relocated from P6 starboard to S4 nadir - deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4794 X = N/A N/A 932 198 152744 Y = 29402 Y = N/A N/A 198 13946 -4




7-314

CONFIGURATION 124

STEP 050



Element Properties: PVRGF (relocated to MBS LEE)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 4356 X = N/A N/A 26 8 1105 Y = -852 Y = N/A N/A 8 32 -7




7-315





Total mass: 464868. lb 210861. kg Center of mass: X Y Z -25.85 -.08 6.35 ft -7.88 -.02 1.93 m Inertia tensor*: slug*ft**2 29897874. 132727. 2464172. 132727. 26477492. -283679. 2464172. -283679. 48236072. kg*m**2 40536056. 179954. 3340967. 179954. 35898644. -384616. 3340967. -384616. 65399304. Principal moments of inertia (IXX, IYY, IZZ): 29580772. 26464361. 48563071. slug*ft**2 40107368. 35881952. 65844696. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -1.09 -7.47 -3.13 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -2.27E+00 -6.57E+00 CPy 6.78E+00 .00E+00 -4.30E+00 CPz -1.23E+01 1.61E-01 .00E+00 X m Y m Z m CPx .00E+00 -6.90E-01 -2.00E+00 CPy 2.07E+00 .00E+00 -1.31E+00 CPz -3.75E+00 4.90E-02 .00E+00 Projected areas: X Y Z 16815.43 8290.58 7031.50 ft**2 1562.20 770.22 653.25 m**2 *Off-diagonal elements are negative integrals



7-316








7-317







7-318





Total mass: 679021. lb 307999. kg Center of mass: X Y Z -6.37 -.06 21.92 ft -1.94 -.02 6.68 m Inertia tensor*: slug*ft**2 48926692. 96877. -11200092. 96877. 62520456. -330654. -11200092. -330654. 66614444. kg*m**2 66335656. 131347. -15185279. 131347. 84766320. -448307. -15185279. -448307. 90317016. Principal moments of inertia (IXX, IYY, IZZ): 43498233. 62506576. 72051264. slug*ft**2 58977488. 84750128. 97691384. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -1.96 25.85 -.19 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -1.91E+00 -1.11E+01 CPy -2.70E+00 .00E+00 -1.09E+01 CPz -2.51E+01 1.60E-01 .00E+00 X m Y m Z m CPx .00E+00 -5.83E-01 -3.39E+00 CPy -8.22E-01 .00E+00 -3.34E+00 CPz -7.65E+00 4.87E-02 .00E+00 Projected areas: X Y Z 20229.24 10184.34 7718.96 ft**2 1879.36 946.16 717.11 m**2 *Off-diagonal elements are negative integrals



7-319

CONFIGURATION 125

STEP 051



�� STS - 117 Space Shuttle Endeavour [OV-105] undocked from ISS.

�� Stage 13A delivered ITS S3 and ITS S4 to ISS.

�� S4 PV radiator was transferred from P6 starboard to S4 nadir using the PVRGF

and the Space Station RMS.

�� The 1A and 3A Solar Arrays were deployed.

�� PVRGF OSE was relocated from S4 truss radiator to MBS LEE. �� P6 truss starboard Solar Array was retracted.



7-320




7-321







7-322





Total mass: 464868. lb 210861. kg Center of mass: X Y Z -25.85 -.08 6.35 ft -7.88 -.02 1.93 m Inertia tensor*: slug*ft**2 29897874. 132727. 2464172. 132727. 26477492. -283679. 2464172. -283679. 48236072. kg*m**2 40536056. 179954. 3340967. 179954. 35898644. -384616. 3340967. -384616. 65399304. Principal moments of inertia (IXX, IYY, IZZ): 29580772. 26464361. 48563071. slug*ft**2 40107368. 35881952. 65844696. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -1.09 -7.47 -3.13 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -2.27E+00 -6.57E+00 CPy 6.78E+00 .00E+00 -4.30E+00 CPz -1.23E+01 1.61E-01 .00E+00 X m Y m Z m CPx .00E+00 -6.90E-01 -2.00E+00 CPy 2.07E+00 .00E+00 -1.31E+00 CPz -3.75E+00 4.90E-02 .00E+00 Projected areas: X Y Z 16815.43 8290.58 7031.50 ft**2 1562.20 770.22 653.25 m**2 *Off-diagonal elements are negative integrals



7-323

CONFIGURATION 126

STEP 052

Stage 13A.1 – After Rendezvous

(STS – 118 on Space Shuttle Columbia)

�� STS-118 Space Shuttle Columbia [OV-102] docks to PMA 2 tail nadir.

�� Stage 13A.1 delivers ITS S5 truss to ISS.


o P5 PVRGF was relocated from the MBS LEE to the stowage position on

ITS P5 keel structure.


o P6 PV forward radiator was retracted.

o S3 CETA light was installed.

o Port SARJ was fixed at 90 degrees, P4 beta gimbals were fixed at 290/70

(2A/4A) degrees.

o Starboard SARJ was fixed at 270 degrees and S4 beta gimbals were fixed

at 300/60 (1A/3A) degrees.

Element Properties: P6 radiator (forward, retracted)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -2854 X = N/A N/A 1015 0 0731 Y = 102 Y = N/A N/A 0 799 0




7-324




7-325



M. Falou/LM/281-333-6326 Stage 13A.1 ISS – After Rendezvous Produced By Contract Item Number


Total mass: 464868. lb 210861. kg Center of mass: X Y Z -25.89 .29 6.35 ft -7.89 .09 1.93 m Inertia tensor*: slug*ft**2 30057630. -57077. 2445761. -57077. 26447964. -228376. 2445761. -228376. 48364416. kg*m**2 40752656. -77386. 3316006. -77386. 35858608. -309637. 3316006. -309637. 65573312. Principal moments of inertia (IXX, IYY, IZZ): 29735812. 26444468. 48686488. slug*ft**2 40317580. 35854980. 66012032. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -.54 -7.49 .47 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -2.55E+00 -6.58E+00 CPy 5.43E+00 .00E+00 -3.16E+00 CPz -1.14E+01 2.12E-01 .00E+00 X m Y m Z m CPx .00E+00 -7.78E-01 -2.00E+00 CPy 1.66E+00 .00E+00 -9.62E-01 CPz -3.47E+00 6.48E-02 .00E+00 Projected areas: X Y Z 16826.91 8033.81 7151.68 ft**2 1563.27 746.37 664.41 m**2 *Off-diagonal elements are negative integrals



7-326



M. Falou/LM/281-333-6326 Stage 13A.1 Orbiter – After Rendezvous Produced By Contract Item Number


Total mass: 233800. lb 106050. kg Center of mass: X Y Z 35.82 -.05 54.78 ft 10.92 -.01 16.70 m Inertia tensor*: slug*ft**2 7985562. -842. 239247. -842. 7690465. -8069. 239247. -8069. 944261. kg*m**2 10826963. -1142. 324375. -1142. 10426866. -10940. 324375. -10940. 1280246. Principal moments of inertia (IXX, IYY, IZZ): 7993435. 7690230. 936103. slug*ft**2 10837974. 10426871. 1269224. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .06 1.94 .21 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 5.16E-02 -9.16E-01 CPy -3.77E+00 .00E+00 -1.10E+00 CPz -1.34E+00 5.09E-02 .00E+00 X m Y m Z m CPx .00E+00 1.57E-02 -2.79E-01 CPy -1.15E+00 .00E+00 -3.35E-01 CPz -4.08E-01 1.55E-02 .00E+00 Projected areas: X Y Z 4393.25 2089.49 740.27 ft**2 408.15 194.12 68.77 m**2 *Off-diagonal elements are negative integrals



7-327



M. Falou/LM/281-333-6326 Stage 13A.1 Mated – After Rendezvous Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0055




7-328



M. Falou/LM/281-333-6326 Stage 13A.1 Mated – After Rendezvous Produced By Contract Item Number


Total mass: 698668. lb 316911. kg Center of mass: X Y Z -5.24 .17 22.55 ft -1.60 .05 6.87 m Inertia tensor*: slug*ft**2 49383716. 42019. -11764671. 42019. 63890540. -158014. -11764671. -158014. 67721352. kg*m**2 66955296. 56971. -15950745. 56971. 86623904. -214239. -15950745. -214239. 91817784. Principal moments of inertia (IXX, IYY, IZZ): 43635545. 63885928. 73468538. slug*ft**2 59163664. 86620336. 99613008. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -.92 26.03 -.10 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -2.09E+00 -1.18E+01 CPy -4.57E+00 .00E+00 -1.03E+01 CPz -2.59E+01 2.83E-01 .00E+00 X m Y m Z m CPx .00E+00 -6.37E-01 -3.59E+00 CPy -1.39E+00 .00E+00 -3.13E+00 CPz -7.88E+00 8.61E-02 .00E+00 Projected areas: X Y Z 20240.71 9936.95 7787.18 ft**2 1880.42 923.17 723.45 m**2 *Off-diagonal elements are negative integrals



7-329

CONFIGURATION 127

STEP 053



�� Space Station RMS attaches the ITS S5 truss to the MBS and then the MT

assembly translates from worksite #3 to worksite #1.

�� SSRMS removes ITS S5 from the MT and berths it to the S3/S4 starboard

interface.

�� CETA cart configuration is CETA A-MT-CETA B.

�� Starboard SARJ is fixed at 254 degrees and S4 beta gimbals are fixed at 180

degrees for S5 installation.



7-330

CONFIGURATION 127

STEP 053



Element Properties: S5 TrussMass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -91 X = 3215 -38554 3037 102 -4561958 Y = 34419 Y = 35324 4139 102 4736 -153

Z = 382 Z = 0 -35320 -456 -153 4843Reference Point Description: Center of keel pin



7-331





Total mass: 469184. lb 212818. kg Center of mass: X Y Z -25.66 2.34 6.28 ft -7.82 .71 1.91 m Inertia tensor*: slug*ft**2 33049558. -958053. 2606293. -958053. 26545916. 22301. 2606293. 22301. 51502288. kg*m**2 44809164. -1298945. 3533657. -1298945. 35991412. 30236. 3533657. 30236. 69827696. Principal moments of inertia (IXX, IYY, IZZ): 32831649. 26400466. 51862203. slug*ft**2 44515100. 35795320. 70317856. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .94 -7.85 8.69 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -5.79E+01 -6.65E+00 CPy 1.08E+01 .00E+00 -4.21E+00 CPz -1.09E+01 1.28E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.77E+01 -2.03E+00 CPy 3.29E+00 .00E+00 -1.28E+00 CPz -3.33E+00 3.91E-01 .00E+00 Projected areas: X Y Z 11288.35 10916.46 7281.35 ft**2 1048.72 1014.17 676.46 m**2 *Off-diagonal elements are negative integrals



7-332





Total mass: 229484. lb 104092. kg Center of mass: X Y Z 35.89 -.05 54.79 ft 10.94 -.02 16.70 m Inertia tensor*: slug*ft**2 7981870. -960. 239626. -960. 7686750. -8118. 239626. -8118. 939256. kg*m**2 10821957. -1301. 324890. -1301. 10421828. -11007. 324890. -11007. 1273459. Principal moments of inertia (IXX, IYY, IZZ): 7989769. 7686514. 931073. slug*ft**2 10833003. 10421832. 1262404. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .06 1.95 .23 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 5.36E-02 -9.26E-01 CPy -3.82E+00 .00E+00 -1.11E+00 CPz -1.40E+00 5.30E-02 .00E+00 X m Y m Z m CPx .00E+00 1.63E-02 -2.82E-01 CPy -1.16E+00 .00E+00 -3.38E-01 CPz -4.27E-01 1.62E-02 .00E+00 Projected areas: X Y Z 4393.25 2074.27 740.27 ft**2 408.15 192.71 68.77 m**2 *Off-diagonal elements are negative integrals



7-333



M. Falou/LM/281-333-6326 Stage 13A.1 Mated - Intermediate 1 Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0056




7-334



M. Falou/LM/281-333-6326 Stage 13A.1 Mated - Intermediate 1 Produced By Contract Item Number


Total mass: 698668. lb 316911. kg Center of mass: X Y Z -5.45 1.55 22.21 ft -1.66 .47 6.77 m Inertia tensor*: slug*ft**2 52327520. -255276. -11453456. -255276. 63646444. 568772. -11453456. 568772. 70613816. kg*m**2 70946560. -346107. -15528794. -346107. 86292952. 771150. -15528794. 771150. 95739440. Principal moments of inertia (IXX, IYY, IZZ): 46813866. 63613440. 76154681. slug*ft**2 63473020. 86250880. 103255040. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: 2.82 25.70 .06 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -4.43E+01 -7.40E+00 CPy -2.00E+00 .00E+00 -1.23E+01 CPz -2.51E+01 1.77E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.35E+01 -2.26E+00 CPy -6.10E-01 .00E+00 -3.74E+00 CPz -7.64E+00 5.39E-01 .00E+00 Projected areas: X Y Z 14703.60 12931.71 7939.99 ft**2 1366.01 1201.40 737.65 m**2 *Off-diagonal elements are negative integrals



7-335

CONFIGURATION 128

STEP 054



�� MT translates from worksite #1 to worksite #4.

�� Remove EAS from P6 and place it on the ICC.

�� Retract the ITS P6 forward radiator.



7-336




7-337





Total mass: 467751. lb 212168. kg Center of mass: X Y Z -25.72 1.01 6.35 ft -7.84 .31 1.93 m Inertia tensor*: slug*ft**2 31548010. -261199. 2588149. -261199. 26509252. -178057. 2588149. -178057. 50004624. kg*m**2 42773340. -354138. 3509057. -354138. 35941704. -241413. 3509057. -241413. 67797136. Principal moments of inertia (IXX, IYY, IZZ): 31202684. 26494839. 50361009. slug*ft**2 42306452. 35923276. 68282448. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -.12 -7.86 2.89 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -5.71E+01 -6.69E+00 CPy 1.08E+01 .00E+00 -4.26E+00 CPz -1.13E+01 1.30E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.74E+01 -2.04E+00 CPy 3.30E+00 .00E+00 -1.30E+00 CPz -3.45E+00 3.96E-01 .00E+00 Projected areas: X Y Z 11276.77 10905.38 7215.68 ft**2 1047.65 1013.14 670.36 m**2 *Off-diagonal elements are negative integrals



7-338








7-339







7-340





Total mass: 698667. lb 316910. kg Center of mass: X Y Z -5.37 .66 22.38 ft -1.64 .20 6.82 m Inertia tensor*: slug*ft**2 50850324. 51417. -11521432. 51417. 63727948. 60854. -11521432. 60854. 69166216. kg*m**2 68943752. 69712. -15620957. 69712. 86403456. 82508. -15620957. 82508. 93776752. Principal moments of inertia (IXX, IYY, IZZ): 45288852. 63726159. 74723766. slug*ft**2 61405316. 86403712. 101314920. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: .06 25.76 .25 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -4.37E+01 -7.54E+00 CPy -2.01E+00 .00E+00 -1.23E+01 CPz -2.55E+01 1.46E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.33E+01 -2.30E+00 CPy -6.13E-01 .00E+00 -3.75E+00 CPz -7.77E+00 4.44E-01 .00E+00 Projected areas: X Y Z 14692.02 12943.53 7874.31 ft**2 1364.93 1202.49 731.55 m**2 *Off-diagonal elements are negative integrals



7-341

CONFIGURATION 129

STEP 055


(STS-118 Space Shuttle Columbia)

�� P6 solar arrays are fixed at 90/270 (2B/4B) degrees.

�� SSRMS unberths the ITS P6 from ITS Z1 and relocates it to the MBS LEE.

�� MT translates from worksite #4 to worksite #8.

�� SSRMS moves the P6 into the overnight park position.

Assumption: A negative hold position for P6 based on a negative ISS Beta Orbit.





7-342

CONFIGURATION 129

STEP 055



Element Properties: P6 Assembly 13A1_I3 (stowed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 4875 X = 4877 -40216 146197 -5178 -76813083 Y = -11863 Y = -17397 16150 -5178 21079 375

Z = -9749 Z = -12011 17401 -768 375 149576Reference Point Description: Center of port, zenith keel pin



7-343





Total mass: 467752. lb 212169. kg Center of mass: X Y Z -23.54 -3.41 6.21 ft -7.17 -1.04 1.89 m Inertia tensor*: slug*ft**2 34526844. 2147204. 3847816. 2147204. 28108954. -1994709. 3847816. -1994709. 54585088. kg*m**2 46812096. 2911216. 5216936. 2911216. 38110608. -2704461. 5216936. -2704461. 74007408. Principal moments of inertia (IXX, IYY, IZZ): 34722302. 27107442. 55387501. slug*ft**2 47078560. 36753880. 75097664. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -6.63 -8.34 -20.39 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -5.46E+01 -6.75E+00 CPy 8.77E+00 .00E+00 -3.13E+00 CPz -9.69E+00 1.35E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.66E+01 -2.06E+00 CPy 2.67E+00 .00E+00 -9.53E-01 CPz -2.95E+00 4.13E-01 .00E+00 Projected areas: X Y Z 11322.15 10577.50 7740.16 ft**2 1051.86 982.68 719.08 m**2 *Off-diagonal elements are negative integrals



7-344








7-345







7-346





Total mass: 698668. lb 316911. kg Center of mass: X Y Z -3.91 -2.30 22.29 ft -1.19 -.70 6.79 m Inertia tensor*: slug*ft**2 53939932. 1186168. -9790595. 1186168. 64120508. -2789295. -9790595. -2789295. 72526760. kg*m**2 73132696. 1608227. -13274258. 1608227. 86935696. -3781774. -13274258. -3781774. 98333040. Principal moments of inertia (IXX, IYY, IZZ): 49732779. 63427922. 77420582. slug*ft**2 67430656. 85999344. 104971424. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -12.82 23.25 -.05 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -4.21E+01 -7.75E+00 CPy -3.18E+00 .00E+00 -1.12E+01 CPz -2.38E+01 4.03E-01 .00E+00 X m Y m Z m CPx .00E+00 -1.28E+01 -2.36E+00 CPy -9.69E-01 .00E+00 -3.41E+00 CPz -7.27E+00 1.23E-01 .00E+00 Projected areas: X Y Z 14798.62 12615.65 8398.79 ft**2 1374.84 1172.03 780.27 m**2 *Off-diagonal elements are negative integrals



7-347

CONFIGURATION 130

STEP 056


(STS – 118 Space Shuttle Columbia)

�� SSRMS maneuvers P6 from the overnight park position and berths it to the port

interface of ITS P5.

�� Deploy P6 PV radiator.



7-348

CONFIGURATION 130

STEP 056



P6 Assembly 13A.1_INT4 (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -162 X = 0 -30799 146201 -7327 137013083 Y = -43682 Y = -38143 7489 -7327 47537 -421

Z = -596 Z = -2845 2501 1370 -421 176395Reference Point Description: Center of port, zenith keel pin



7-349

CONFIGURATION 130

STEP 056



Element Properties: P6 PV radiator - 13A.1_INT4 (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -4616 X = N/A N/A 940 174 149731 Y = -44721 Y = N/A N/A 174 13601 -3




7-350




7-351





Total mass: 467752. lb 212169. kg Center of mass: X Y Z -24.72 -11.17 8.37 ft -7.53 -3.41 2.55 m Inertia tensor*: slug*ft**2 51924736. 4305126. 2442886. 4305126. 25521984. -2094284. 2442886. -2094284. 72418600. kg*m**2 70400456. 5836964. 3312107. 5836964. 34603148. -2839467. 3312107. -2839467. 98186392. Principal moments of inertia (IXX, IYY, IZZ): 52392831. 24710559. 72757285. slug*ft**2 71037312. 33504044. 98648648. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -2.97 -5.88 -9.56 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -5.00E+01 -7.30E+00 CPy 9.92E+00 .00E+00 -5.23E+00 CPz -9.13E+00 -4.42E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.52E+01 -2.23E+00 CPy 3.02E+00 .00E+00 -1.59E+00 CPz -2.78E+00 -1.35E+00 .00E+00 Projected areas: X Y Z 11601.60 10570.49 8176.96 ft**2 1077.82 982.03 759.66 m**2 *Off-diagonal elements are negative integrals



7-352








7-353







7-354





Total mass: 698668. lb 316911. kg Center of mass: X Y Z -4.70 -7.50 23.73 ft -1.43 -2.29 7.23 m Inertia tensor*: slug*ft**2 70894160. 1067040. -10845294. 1067040. 61230512. -4587337. -10845294. -4587337. 91581096. kg*m**2 96119536. 1446711. -14704238. 1446711. 83017392. -6219591. -14704238. -6219591. 124167240. Principal moments of inertia (IXX, IYY, IZZ): 66364769. 60508121. 96825945. slug*ft**2 89981296. 82040504. 131282368. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -10.71 21.70 8.63 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.96E+01 -8.24E+00 CPy -2.41E+00 .00E+00 -1.26E+01 CPz -2.39E+01 -6.94E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.21E+01 -2.51E+00 CPy -7.34E-01 .00E+00 -3.83E+00 CPz -7.29E+00 -2.12E+00 .00E+00 Projected areas: X Y Z 15075.71 12608.64 8833.54 ft**2 1400.58 1171.38 820.66 m**2 *Off-diagonal elements are negative integrals



7-355

CONFIGURATION 131

STEP 057



�� Deploy P6 channels 2B and 4B solar arrays.

�� Translate MT from worksite #8 to worksite #4.

�� Relocate the SSRMS from MBS to Destiny Lab.

�� Port SARJ is fixed at 90 degrees. P4 beta gimbals are fixed at 290/70 (2A/4A)

degrees.

�� Starboard SARJ is fixed at 270 degrees, and S4 beta gimbals are fixed at 300/60

(1A/3A) degrees.



7-356

CONFIGURATION 131

STEP 057



Element Properties: P6 Assembly 13A.1_BS (deployed)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -162 X = 0 -30799 146201 -7327 137013083 Y = -43682 Y = -38143 7489 -7327 47537 -421

Z = -596 Z = -2845 2501 1370 -421 176395Reference Point Description: Center of port, zenith keel pin

P6 Solar Array (POA) Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 548 X = 547 -30799 184491 3 -911062 Y = -47939 Y = -47912 7489 3 176381 -19

Z = -14791 Z = -1806 2501 -91 -19 8317Reference Point Description: N/A

P6 Solar Array (POF) Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = -705 X = -775 -30799 180359 -1 16731059 Y = -47911 Y = -47912 7489 -1 171792 15

Z = 13257 Z = 1102 2501 1673 15 8787Reference Point Description: N/A

Space Station RMS (relocated from MBS to Destiny Lab)Mass Center of Mass Reference Point Inertia Tensor[kg] [mm] ISS [mm] RSA [mm] [kg*m^2]

X = 73 X = N/A N/A 8503 -366 37851502 Y = -710 Y = N/A N/A -366 10308 2238




7-357



M. Falou/LM/281-333-6326 Stage 13A.1 ISS – Before Separation Produced By Contract Item Number





7-358



M. Falou/LM/281-333-6326 Stage 13A.1 Orbiter – Before Separation Produced By Contract Item Number





7-359



M. Falou/LM/281-333-6326 Stage 13A.1 Mated – Before Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0060




7-360



M. Falou/LM/281-333-6326 Stage 13A.1 Mated – Before Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-MP0119


Total mass: 696905. lb 316111. kg Center of mass: X Y Z -4.86 -6.39 23.92 ft -1.48 -1.95 7.29 m Inertia tensor*: slug*ft**2 69939960. 709355. -10986141. 709355. 61353596. -3922930. -10986141. -3922930. 90153640. kg*m**2 94825808. 961755. -14895201. 961755. 83184272. -5318776. -14895201. -5318776. 122231872. Principal moments of inertia (IXX, IYY, IZZ): 65309250. 60717582. 95413504. slug*ft**2 88550160. 82324504. 129367296. kg*m**2 Principal to body roll, pitch, yaw in a 1 2 3 sequence: -11.36 21.65 12.63 degrees Center of pressure: (WRT CM) X ft Y ft Z ft CPx .00E+00 -3.58E+01 -1.51E+01 CPy -4.80E+00 .00E+00 -9.71E+00 CPz -2.45E+01 -9.08E+00 .00E+00 X m Y m Z m CPx .00E+00 -1.09E+01 -4.60E+00 CPy -1.46E+00 .00E+00 -2.96E+00 CPz -7.46E+00 -2.77E+00 .00E+00 Projected areas: X Y Z 26516.47 9521.85 8602.35 ft**2 2463.46 884.61 799.18 m**2 *Off-diagonal elements are negative integrals



7-361

CONFIGURATION 132

STEP 058

Stage 13A.1 – After Separation


�� STS-118 Space Shuttle Columbia [OV-102] undocked from the PMA 2 docking

port.

�� Stage 13A.1 delivered ITS S5 truss to the ISS.

�� EAS was moved from P6 to the ICC for return.

�� P6 was removed from Z1 and berthed to P5.

�� P6 PV radiator and channels 2B and 4B solar arrays were deployed.

�� MT translated to worksite #4.

�� SSRMS was relocated from MBS to Destiny lab.



7-362




7-363



M. Falou/LM/281-333-6326 Stage 13A.1 ISS – After Separation Produced By Contract Item Number Brad Henry NAS9-19100 Science Engineering Analysis & Test 02-DR0061




7-364



M. Falou/LM/281-333-6326 Stage 13A.1 ISS – After Separation Produced By Contract Item Number





APPENDICES



A-1

APPENDIX A

ACRONYMS AND ABBREVIATIONS A A American A/R American/Russian APAS Androgynous Peripheral Attach System APFR Articulating Portable Foot Restraint AR After Rendezvous AS After Separation B BS Before Separation BSP Band Signal Processor C CAD Computer Aided Design CBM Common Berthing Mechanism CETA Crew and Equipment Translation Assembly cm Centimeter CM Center of Mass CP Center of Pressure CSA Canadian Space Agency D DAC Design Analysis Cycle DC Docking Compartment DCN Design Change Notice DCSU DC Switching Unit DDCU Direct current-to-Direct current Converter Unit DY day E EA4 System Engineering Office [NASA/JSC] EAS Early Ammonia Servicer EATCS External Active Thermal Control System ECOMM Early Communication System EDS Electronic Data Systems EEATCS Early External Active Thermal Control System ESA European Space Agency ESP External Stowage Platform ETSD EVA Tool Stowage Device ETVCG External Television Camera Group EV-CPDS Extravehicular-Charged Particle Detection System EVA Extravehicular Activity



A-2

F FGB Functionalni Gruzvoi Blok [Russian] FHRC Flex Hose Rotary Cupler FSE Flight Support Equipment FPMU Field Plasma Measurement Unit ft feet ftp File Transfer Protocol H HD Highly Directional HPGA High Pressure Gas Assembly HPGT High Pressure Gas Tank HR hour http hypertext transfer protocol I I-DEAS Integrated Design Engineering Analysis Software ICC Integrated Cargo Carrier IDD Interface Development Document IGES International Graphics Exchange Standard INT Intermediate ISS International Space Station ISSP International Space Station Program ITA Integrated Truss Assembly ITS Integrated Truss Segment J JSC (Lyndon B.) Johnson Space Center JTWG Joint Technical Working Group K kg kilogram KhSC Khrunichev State Research and Production Space Center L lb pound LCA Lab Cradle Assembly LDA Launch Deployment Assembly LEE Latching End Effector LM Lockheed Martin LMSO Lockheed Martin Space Operations LVLH Local Vertical/Local Horizontal M m meter



A-3

MBS MRS Base System MBSU Main Bus Switching Unit MDM Multiplexer/De-Multiplexer MIN minute MISSE Materials ISS Experiment mm millimeters MN minute MOD Mission Operations Directorate MODGEN Model Generator MPAC Micro-Particle Capture MPLM Multi-Purpose Logistics Module MPSU Main Bus Switching Unit MPSET Mass Properties Sustaining Engineering Tool MPVSET Mass Properties Verification and Sustaining Engineering Tool MRS Mobile Remote Servicer MT Mobile Transporter MTS Mobile Truss Structure MTSAS Module Truss Structure Attach System N N/A Not Applicable NASA National Aeronautics and Space Administration [United States] NASDA National Space Development Agency [Japan] NSTS National Space Transportation System O ODS Orbiter Docking System OM ISS Mission Integration Office (organization code) OMS Orbital Maneuvering System ORU Orbital Replacement Unit OSE Orbital Support Equipment OSRS Orbiter Structural Reference System OTD ORU Transfer Device OV Orbiter Vehicle P P Progress; Port P1 Port 1 PDGF Power and Data Grapple Fixture PFCS Pump and Flow Control Subassembly PIA Port Inboard Aft PIF Port Inboard Forward PIT Physical Integration Team [Boeing] PMA Pressurized Mating Adapter POA Port Outboard Aft POF Port Outboard Forward



A-4

PROP Propellant PV Photovoltaic PVR PV forward Radiator PVRGF Photovoltaic Removable Grapple Fixture PWP Portable Work Platform R R Russian RAI Resource Analysis and Integration Rev Revision RM Resource Management RMS Remote Manipulator System RPO Research Program Office RSA Russian Space Agency RSC-E Rocket Space Corporation-Energia S S Soyuz SARJ Solar Alpha Rotary Joint SASA S-band Antenna Structural Assembly SDRC Structural Dynamics Research Corporation SEC second SEED Space Environment Exposure Device SEMDA Systems Engineering, Modeling, and Design Analysis SGANT Space to Ground Antenna SHOSS Spacehab Oceaneering Space System SIA Starboard Inboard Aft SIF Starboard Inboard Forward SLP Spacelab Pallet SMDP Service Module Debris Panel SMDS Service Module Debris Shields SODB (Space) Shuttle Operational Data Book SPP Science Power Platform SSACS Space Station Analysis Coordinate System SSCB Space Station Control Board SSP Space Shuttle Program SSRMS Space Station Remote Manipulator System STS Space Transportation System T TCS Thermal Control System TIM Technical Interchange Meeting TM Transport Spacecraft, Modified TUS Trailing Umbilical System



A-5

U UF Utilization Flight UHF Ultra High Frequency UIS Universal Instrument Section ULCAS Unpressurized Logistics Carrier Attach System ULF Utilization Logistic Flight UT Universal Translator V VAC Verification Analysis Cycle VIPeR Vehicle Integrated Performance and Resources [team] VMDB Vehicle Management Database VSSA Video Stanchion Support Assembly W WETA WVS External Transceiver Assembly WRT with respect to WVS Wireless Video Systems X, Y, Z Z1 Zenith 1



A-6




B-1

APPENDIX B COMPONENT DEFINITIONS

PREFIXES P1 First port truss section, outboard of the middle truss section

P3 Second port truss section, outboard of P1

P4 Third port truss section, subject to alpha rotation

P5 Fourth port truss section, subject to alpha rotation

P6 Fifth port truss section (subject to alpha rotation)

PIA Port inboard aft

PIF Port inboard forward

POA Port outboard aft

POF Port outboard forward

S0 Zero, or Middeck truss section, formerly called M1

S1 First starboard truss section, outboard of middle ITA

S3 Second starboard truss section, outboard of S1

S4 Third starboard truss section, subject to alpha rotation

S5 Fourth starboard truss section, subject to alpha rotation

S6 Fifth starboard truss section, subject to alpha rotation

SIA Starboard inboard aft

SIF Starboard inboard forward

SOA Starboard outboard aft

SOF Starboard outboard forward

Z1 Zenith, first truss section on Node 1



B-2

COMPONENT DEFINITIONS (continued) SUFFIXES

xx_AS

After Separation: A free-flying configuration immediately after Orbiter or Progress vehicle undocking.

xx_AR

After Rendezvous: An Orbiter-attached configuration immediately after docking and before payloads unloaded, a Space Shuttle mission phase.

xx_INTx

Intermediate: An Orbiter-attached configuration partially unloaded, a potential Space Shuttle mission phase. A number after ‘INT’ designates one of multiple intermediate configurations. No number indicates that a single intermediate configuration exists.

xx_BS

Before Separation: An Orbiter-attached configuration immediately before undocking and after payloads unloaded, a Space Shuttle mission phase.

xS_ARx

Soyuz Relocation: A configuration after a Soyuz undocks, moves to another location, and re-docks to the ISS. The number before ‘S’ indicates the stage that the Soyuz vehicle was launched.



C-1

APPENDIX C DATA BOOK SPECIFICATIONS

ITEM VARIABLE SPECIFICATION

VOLUMES TWO I and II

VERSION NUMBER JSC 26557 REVISION P; VOLUME I and II

VERSION NUMBER LESC 31166 REVISION P; VOLUME I and II

MANUAL SOFTWARE MICROSOFT WORD 2000

COVER FONT SIZE Arial 10, 12,18, 20, 24-point

PAGE SIZE 8 ½-inch X 11-inch

PAGE FORMAT Portrait and Landscape (Figures or Tables) LOGO NASA MICROSOFT WORD

LOGO LOCKHEED MARTIN MICROSOFT WORD

TEXT ACRONYMS Identified once at first use only

TEXT FONT Arial 12-point

TEXT HEADINGS No Bold; no underlines; ALL CAPS; Left

TEXT MARGINS Left: 1.2-inches; others 1-inch; mirror pages

TEXT SPACING Flush left; ragged right

TEXT INDENT ¼-inch then ½-inch

TEXT LISTS Bullets unless order is required

TABLES TITLE/TEXT Title at top; Arial 10-point

FIGURES TITLE/TEXT Title at bottom; Arial 12-point

HEADER RIGHT CORNER JSC Document number, revision, volume

REFERENCE DOCUMENT/SOFTWARE Italics

FOOTER RIGHT CORNER LESC Document number, revision, volume

FOOTER PAGE NUMBERS 1-1, 2-1, 3-1, 4-1, 5-1, 6-1, 7-1

FOOTER APPENDICES PAGES A-1, B-1, C-1, IND-1

HEADER/FOOTER FONT SIZE Arial 9-point

PAGE Blanks “This page included for formatting purposes.”



C-2




D-1

APPENDIX D Solar Array and SARJ Rotational Conventions

270

90

180

0

270

180

0

90

n

n P6-LWR-4B US Array

P6-UPR-2B US Array

Figure D-1 US Solar Array Conventions Phase 1 Complete



D-2

90

0

180

270

��

90

270

0

180

��

270

180

0

90��

90

180

0

270

��

270

0

180

90

��

90

0

180

270��

n

n

nn

n

n

nn

2B

4B2A

4A

1A

3B

1B3A

0-90

90

��

Figure D-2 US Segment Solar Array & Radiator Conventions Assembly Complete



E-1

APPENDIX E

Worksite Naming Conventions

Table E-1 Naming Convention for the MT Worksites

WORKSITE BOEING ITS BAY MOD ITS BAY ISS ITS BAY

W orksite #1 S3B2 S3B2 S3B17W orksite #2 S1B2 S1B2 S1B13W orksite #3 S1B6 S1B6 S1B5W orksite #4 S0B2 S0B2 S0B1W orksite #5 S0B5 S0B5 S0B4W orksite #6 P1B6 P1B1 P1B6W orksite #7 P1B2 P1B5 P1B14W orksite #8 P3B2 P3B1 P3B18W orksite #9 S6B? S6B? S6B?W orksite #10 P6B? P6B? P6B?

NOMENCLATURE



E-2
