Taxial = = 6- PA PiLi AE Ai Ei My Bending = I T = GY = VQ T= ; Q = Ay T = 2qA It q=tt Ultimate Load FOS = KT = Allowable Load Area of a circle Acircle = r 71 T GJ L Circumference of a circle Ccircle = 2r = TL = GJ = P My A I TL S1 4AG + t Sn tn Question 3: The centreline dimensions of the thin-walled cross section of an aircraft pressurized fuselage of length of 7 m are shown in the Figure. The fuselage is made of 2014-T6 aluminium alloy having ultimate shear strength of 290 MPa and is subjected to a torque of 8135 N.m. For pressurized fuselage a 2.0 safety factor is usually applied. 1.37 m 0.91 m 0.91 m (a) What type of construction is used in modern aircraft fuselage structure? What are the major components of a fuselage's basic structure and their functions? What type of loads should the fuselage structure support? (b) Calculate the allowable shear strength. (c) Calculate the thickness t? (d) Using the thickness t result obtained in part (c), calculate the angle of twist of the aircraft fuselage section in radian. (Assume shear modulus, G = 28 GPa). (e) What does torsional stiffness mean? What conclusion can you draw about the torsional stiffness of the fuselage based on the angle of twist finding?