1. STRUCTURES & WEIGHTS QDR 1
TEAM 4
Jared Hutter, Andrew Faust, Matt Bagg, Tony Bradford,
Arun Padmanabhan, Gerald Lo, Kelvin Seah
October 16, 2003

2. OVERVIEW Material Properties Wing Analysis C.G. Location Estimation
V-n Diagram
Load Distribution
Shear Distribution
Bending Moment Distribution
C.G. Location Estimation
Follow-Up Action

3. Modulus of Elasticity (ksi)
Material Properties
Material
Density (lb/ft3)
Modulus of Elasticity (ksi)
Yield Stress (psi)
Shear Modulus (ksi)
Foam
1.5
460 – 500
Al 6061-T6
5.2
10400
40000
3900
Balsa 11
625
1725
24070
Spruce 34
1500
8600
Plywood 37
800
4000
Carbon Fiber
109.2
33360
OTHERS
Epoxy: oz/in2
Monokote: oz/in2
Fiber Glass: oz/in2

4. Wing Analysis Load Limit at Max Speed 1-g at Level Flight Stall Speed
CLmax Constraints
Structural Constraints

5. Wing Analysis
Calculations based on Schrenk’s Approximation (Raymer, p. 413)
Rectangular planform.

6. Shear decreases from root to tip.
Wing Analysis
Shear decreases from root to tip.

7. Bending moment decreases from root to tip.
Wing Analysis
Bending moment decreases from root to tip.

8. C.G. LOCATION ESTIMATION
This figure shows the approximate weights and C.G. locations of the main components: x
Wing
W = lb
x = 1.55 ft
Avionics Pod
W = 20 lb
x = ft
Tail Booms
W = 4.04 lb
x = 5.0 ft
Tail Section
W = 2.8 lb
x = 8.87 ft
Engines, Fuel, Casings
& Landing Gears
W = lb
x = 0 ft
NOT TO SCALE

9. C.G. LOCATION ESTIMATION
LIFT x
Total Weight: W = 54.6 lb
C.G. Location: x = 0.65 ft
Wing M.A.C.: x = ft
Static Margin: SM = 4.0%
WEIGHT
SM = – (xCG – xMAC) / c
NOT TO SCALE

10. FOLLOW-UP ACTIONS Geometric layout of wing structure.
Landing gear design.
Moments and products of inertia.

11. QUESTIONS?