dlr presentation

8/3/2019 DLR Presentation

http://slidepdf.com/reader/full/dlr-presentation 1/22



A wing is an appendage with a surface thatproduces lift for flight and/or propulsionthrough the atmosphere, or through anothergaseous or liquid fluid.

It is an airfoil which has a streamlinedcross-sectional shape producing a useful liftto drag ratio.

The wing deflects air downward as theaircraft moves forward generating liftingforce to support the aircraft in flight.



DLR F6 is and

modified version of

DLR F4 with an aim

to have moreelliptical lift

distributions and less

boundary layer

separation at rear

upper wing surface.



FAIRCHILD DORNIER

728

AIRBUS A380



AIRBUS A320

EMBRAER 170



BOMBARDIER CRJ700

BASELINE ARJ21-700



UPPER SKIN - 7075 T6 Aluminum

•Composition:

Al 87.1-91.4% Fe Max 0.5Zn 5.1-6.1% Cr 0.18-0.28%Mg 2.1-2.9% Mn Max 0.3

Cu 1.2-2% Si Max 0.4Ti Max 0.2%Other, each max 0.05%-E = 71.71 Gpa -ρ=2810 kg/m 3

- ν= 0.33

•Properties: Better compressivestrength, high stiffness, fatigue

resistant.



LOWER SKIN 2024-T3

•Composition: Al 90.7-94.7% Mg 1.2-1.8%

Cr Max 0.1% Mn 0.3-0.9%Cu 3.8-4.9% Si Max 0.5%

Fe Max 0.5% Ti Max 0.15%Zn Max 0.25%Others, each max 0.05%-E=73.1 Gpa -ρ=2780 kg/m 3

- ν= 0.33

•Properties: Better tensile strength,fatigue resistant.



•Front spar location 10 % of chord

Reason:

- Lightning effect- Increasing the area of wing box- Forward location would increase the c/s area of wing

box, but would result in reduction of web length.

•Rare spar location 70% of chord

Reason:

- Leaving sufficient space for control surfaces.- Rearward shift of spar would increase the wing boxc/s but would result in reduction of spar web length.



OBJECTIVE 1: PLACEMENT OF FUEL TANK

-MAX FUEL CAPACITY : 24200 LT

-FUEL TANK DESIGNED FOR – 20,000 LT



OBJECTIVE 2: RIB LOCATIONS

- RIBS PLACED AT ROOT , KINK AND TIP

- DEFLECTION OF EACH PLATE BETWEEN RIBS

MINIMIZED TO 5 MM

- TOTAL NUMBER RIBS PLACED IN BETWEEN KINK TO TIP 16

- TOTAL NUMBER OF RIBS PLACED IN

BETWEEN ROOT TO KINK 9



CALCULATIONS FOR RIB PLACEMENT:

SPECIFICATIONS:

MATERIAL – 7075 T6 AL

YOUNGS MODULUS E = 71.71 GPA

POISSONS RATIO = .33MATERIAL THICKNESS T = 5 MM

LOAD CURVE EQUATION =

Y = -3.207X2+ 49.92X + 678.74



METHOD USED :

ITERATION METHOD

ASSUMPTIONS MADE :

-PLANE SECTIONS IN PLATE REMAIN PLANE EVEN AFTER BENDING -PLATES ARE APPROXIMATED TO RECTANGULAR PLATES -LOAD IS APPROXIMATED TO UNIFORM TRANSVERSE LOAD

-SPAR

AND

RIB

DEFLECTIONS

ARE

NEGLECTED

- PLATES ARE ASSUMED TO BE CLAMP SUPPORTED ON ALL THE EDGES



FORMULA USED FOR CALCULATING THE

AMPLITUDE OF DEFORMATION :

w= DEFORMATION IN Z DIRECTIONq = TRANSVERSE LOAD

ξ - x/a a -LENGTH OF PLATE IN X DIECTION

η - y/ b b -LENGTH OF PLATE IN Y DIRECTION

A – AMPLITUDE OF DEFLECTION



RIBS PLACEMENT FROM KINK TO

TIP



RIB PLACEMENT FROM ROOT TO KINK



-Aircraft structures ,T H G MEGSON-Structural stability of columns and plates,Iyengar N.G.R.

-synthesis of subsonic aircraft design , H Wittenberg

dlr presentation

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