Question 8 (15 Marks) a) b) c) (i) (ii) (iii) The aerodynamic load distribution acting on the wing of the aircraft can be approximated by a distributed load acting on the

main spar of the wing as shown below: 3600 N/m hy C fay m₂ 8-30⁰ B The wing is level and is supported by a strut at point B making and angle = 30° with the main spar. Formulate a 3 element beam bending model and 1 element truss model to represent the loading of the aircraft. Hence, use this model to appraise the shear force and bending moment that is acting on the main spar at point B. Where the element stiffness matrix for beam element is : 12 6L 12 6L V 41² -6L 212 ₂ EI 6L L-12 -6L 12 -6L 6L 21² -6L 4L² ₂ D And the element stiffness matrix for truss element is : AE 1 (-40-0 Assume that the spar has a constant cross section where El is constant Construct the stiffness matrix for each of the beam element Construct the stiffness matrix for the truss element Develop and assemble the stiffness matrix of the entire wing spar Assume all nodal loads are given, defined the boundary condition for solving the global equation What are the possible choice of numerical method could be employed or designed to solve the equation?