2) Assume that the fuselage weighs 220,000N and that the payload plus fuel weighs 310,000N. This total
weight of 530,000N shall be evenly distributed over the length of the fuselage. The wing plus engines
shall weigh 90,000N and act at the fuselage half-point.
a) Using the coordinate system in the figure, provide accurate drawings ("x-y figures") of the y-shear
force and the z-bending moment (to scale, with labels etc.).
b) What is the maximum fuselage bending moment?
c) The limit load factor shall be 2.5. The safety factor shall be 1.5. What is the design load factor?
d) For what maximum bending moment in Nm would you design the fuselage?