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Question 4: Slope deflection analysis (15 marks] The wing of an aircraft (structure ABC) comprises of the main wing-box BC and a sharklet AB oriented with a degrees to the horizontal direction as shown in Figure 94. The aerodynamic loading is idealised as uniformly distributed loading with magnitude of w for the main wingbox and w for the sharklet. The value of both the loading and geometric parameters are given in Figure 04. Ignoring the effects of axial forces and using slope deflection method address the following: a) Obtain the value of displacement and rotation at point B assuming a clamped boundary condition for wing-fuselage interface. Note: You may use MathCAD or Excel to solve system of equations and use any justified assumptions along the way. You may need to approximate the solution but justification must be presented. [8 marks] b) Draw both shear force and bending moment diagram for the main wing-box, i.e. structure BC. [7 marks) W L = 36000mm I I = 2400mm E = 70000 MPa 110 mm W-40N / w=20N/m a = 60 deg 201711111 W B 0.5E1 2 ET Figure Q4: Graphical illustration of the aircraft of study