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

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

Modulus of Elasticity (ksi) Material Properties Material Density (lb/ft3) Modulus of Elasticity (ksi) Yield Stress (psi) Shear Modulus (ksi) Foam 1.5 320 - 360 460 – 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: 0.007 oz/in2 Monokote: 0.0021 oz/in2 Fiber Glass: 0.0937 oz/in2

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

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

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

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

C.G. LOCATION ESTIMATION This figure shows the approximate weights and C.G. locations of the main components: x Wing W = 12.04 lb x = 1.55 ft Avionics Pod W = 20 lb x = -1.41 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 = 15.72 lb x = 0 ft NOT TO SCALE

C.G. LOCATION ESTIMATION LIFT x Total Weight: W = 54.6 lb C.G. Location: x = 0.65 ft Wing M.A.C.: x = 0.775 ft Static Margin: SM = 4.0% WEIGHT SM = – (xCG – xMAC) / c NOT TO SCALE

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

QUESTIONS?