AE 215 Homework #7 Due 11/10/2006 (Fri) 1. Bedford/Liechti problem 7-1.5 2. Bedford/Liechti problem 7-2.15 3. Bedford/Liechti problem 7-2.20 4. The figure below shows an aircraft wing that is cantilevered from the fuselage (not shown) at location A. The wing has self–weight that can be approximated by the distributed loadw(x) = −wo(1− xa+b) withwo = 100 lb/ft, a = 10 ft andb = 20 ft. The wing has a small tip tank with weight, Wt = 200 lb, at location C. The wing supports an engine pod with weight, We = 1500 lb, hanging under the wing at B. During a stationary run–up on the ground, the engine also produces a torque, Te = 2500 ft-lb. A tip tank engine wing C x y L a A B C x y w(x) W t W e T e B (a) Write analytic expressions (symbolically, no numbers) for the shear force, V(x), and the bending moment, M(x), distributions in the wing in terms of the given parameters. (b) Sketch the shear force and bending moment diagrams, V(x) and M(x). Label all interesting points with numeric values. 5. An overhang beam of length, L=10 feet, rectangular cross–section (b = 1 in, h = 2 in), and modulus, E = 107 psi, is loaded with a tip load, P = 1000 lbs. (a) Sketch the shear force diagram, V(x), and bending moment diagram, M(x), and label all significant points with numeric values. (b) Specify the location and value of the maximum tensile stress, σmax. M B = 2 P L A B C D P L/4 L/2 L 6. Bedford/Liechti problem 8-1.2 7. Bedford/Liechti problem 8-1.3 8. Bedford/Liechti problem 8-1.14