dlr presentation
TRANSCRIPT
8/3/2019 DLR Presentation
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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.
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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.
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FAIRCHILD DORNIER
728
AIRBUS A380
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AIRBUS A320
EMBRAER 170
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BOMBARDIER CRJ700
BASELINE ARJ21-700
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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.
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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.
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•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.
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OBJECTIVE 1: PLACEMENT OF FUEL TANK
-MAX FUEL CAPACITY : 24200 LT
-FUEL TANK DESIGNED FOR – 20,000 LT
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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
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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
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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
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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
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RIBS PLACEMENT FROM KINK TO
TIP
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RIB PLACEMENT FROM ROOT TO KINK
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-Aircraft structures ,T H G MEGSON-Structural stability of columns and plates,Iyengar N.G.R.
-synthesis of subsonic aircraft design , H Wittenberg