1) In the thin composite panel reinforced with the fibers shown below, the volume percentage of the fibers stacked continuously and in the same direction is 60% and the matrix 40%. Axial Young's Modulus of Fibers: EF = 105 x 109 N/m2 (106 GPa) and the matrix Em = 3.2 x 109 N/m2 (3.2 GPa). On composite panel In service conditions, the load in the 1-direction is 4 tons (4000 kg) and in the 2-direction 5 tons (5000 kg). As a result, the composite panel elongates by 1 mm along its 1-axis and by 2.2 mm along its 2-axis. The length of the panel (along its 1-axis) is 200 cm, its width (along its 2-axis) is 100 cm and its thickness is 4 mm. The resulting shear stress is 22 MPa (22 x 106 N/m2). Accordingly and using the shape: (45 points) a) Find the stress and deformation values of the composite panel. When making this calculation, please state any symmetry and/or approach you suggest with justification. b) Find the reduced stiffness [Q] and compliance [S] matrices for the loading conditions along the principal axes, calculate their numerical values and represent them in matrix form. c) Write the matrix values in b) in terms of engineering constants and calculate the numerical values of the engineering constants. d) Calculate the stress and strain values for the off-axis loading ( = 45) in the x-y axis set in the figure. (Note: g = 9.81 m/s2 1 MPa = 106 N/m2 1 GPa = 109 N/m2)