2. Consider a small conventional aircraft with a maximum mass of 1000 kg. The structure of that a/c is being designed for a limit load factor of 3. 5 marks a) What is the total lift L (in N) corresponding to the above load factor? b) Knowing that it is the largest bending moment applied to the wing structure when safety factors are taking into consideration, determine the location of the wing design bending moment relative to the wing planform and list all the possible loads on the wing that would typically influence the magnitude of this moment. 5 marks c) Assuming that the above design moment is solely due to the ultimate lift force on each wing (0.5Lult), determine its magnitude in N.m. Take the wing load bearing structure to be a straight cantilever beam 9 m long and assume the resultant lift force to act at 1/3 that distance from the wing root (see graphic left side). 5 marks d) Assuming the wing beam is of rectangular (hxw), thin wall cross section of uniform wall thickness t (see graphic right side), select an appropriate methodology to determine that wall thickness. In answering this question you must list the appropriate engineering principles and equations and state how you would use them to obtain t. You must also clearly state and justify simplifying assumptions, if any. 5 marks e) Apply the above methodology to obtain the thin wall thickness t if h=120 mm and w=550 mm and if the maximum applied stress is not to exceed 280 MPa. 15 marks 0.5 Lult W 9 m Beam's cross section