AAE 451 STRUCTURES WEIGHTS QDR 1 TEAM 4

AAE 451 STRUCTURES & WEIGHTS QDR 1 TEAM 4 Jared Hutter, Andrew Faust, Matt Bagg, Tony Bradford, Arun Padmanabhan, Gerald Lo, Kelvin Seah October 16, 2003

TEAM 4 OVERVIEW n Material Properties n Wing Analysis ¨ V-n Diagram ¨ Load Distribution ¨ Shear Distribution ¨ Bending Moment Distribution n C. G. Location Estimation n Follow-Up Action

TEAM 4 Material Properties Material Density (lb/ft 3) Modulus of Elasticity (ksi) Foam 1. 5 320 - 360 Al 6061 -T 6 5. 2 10400 40000 3900 Balsa 11 625 1725 24070 Spruce 34 1500 8600 Plywood 37 800 4000 Carbon Fiber 109. 2 33360 OTHERS Yield Stress (psi) Shear Modulus (ksi) 460 – 500 n Epoxy: 0. 007 oz/in 2 n Monokote: 0. 0021 oz/in 2 n Fiber Glass: 0. 0937 oz/in 2

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

TEAM 4 Wing Analysis n Calculations based on Schrenk’s Approximation (Raymer, p. 413) n Rectangular planform.

TEAM 4 Wing Analysis Shear decreases from root to tip.

TEAM 4 Wing Analysis Bending moment decreases from root to tip.

C. G. LOCATION ESTIMATION n TEAM 4 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 Engines, Fuel, Casings x = -1. 41 ft & Landing Gears W = 15. 72 lb x = 0 ft NOT TO SCALE Tail Booms W = 4. 04 lb x = 5. 0 ft Tail Section W = 2. 8 lb x = 8. 87 ft

C. G. LOCATION ESTIMATION TEAM 4 LIFT x n WEIGHT n n n NOT TO SCALE Total Weight: C. G. Location: Wing M. A. C. : Static Margin: SM = – (x. CG – x. MAC) / c W = 54. 6 lb x = 0. 65 ft x = 0. 775 ft SM = 4. 0%

FOLLOW-UP ACTIONS TEAM 4 n Geometric layout of wing structure. n Landing gear design. n Moments and products of inertia.

AAE 451 QUESTIONS?