Consider a twin-turboprop military aircraft with a maximum take-off mass of 3200 kg and wing area of 28 m 2 m 2 . The fuselage has a length of 11 m, a maximum diameter of 1.3 m, and a mass of 290 kg....

Consider a twin-turboprop military aircraft with a maximum take-off mass of 3200 kg and wing area of 28 m²
m². The fuselage has a length of 11 m, a maximum diameter of 1.3 m, and a mass of 290 kg. Model the fuselage as a thin cylindrical shell and determine its longitudinal, lateral, and directional mass moment of inertia about the aircraft cg. Assume that the aircraft cg is along the fuselage center line and located at 6 m from the fuselage nose.