Question 1: Design of Composite Wing [20 Marks] Your company is performing preliminary design of a composite wing struct

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Question 1 Design Of Composite Wing 20 Marks Your Company Is Performing Preliminary Design Of A Composite Wing Struct 1 (56.23 KiB) Viewed 33 times

Question 1: Design of Composite Wing [20 Marks] Your company is performing preliminary design of a composite wing structure. The materials department has characterised the compression after impact (CAI) strength of two laminates, with aerospace notation of (60/30/10) and (20/60/20). Which laminates would be most suitable for: a) Stiffeners (stringers) of wing covers? [1 mark) b) Shear web of the spars? [1 mark] c) Explain your reasoning. Note: Use maximum 50 words. [2 marks] A composite laminate is designed as [+45°,0,90]s. It is to be manufactured using 1700 carbon fibres with E765 resin, with a cured ply thickness of 0.125mm. The global finite element model calculates the ultimate running load at the laminate to be Nx = 1200 N/mm, Ny = 100 N/mm and Nxy = 500 N/mm. Using ElamX, calculate the following: d) The equivalent membrane stiffness constants of the laminate (including Poisson's ratio effects) Ex, Ey and Gxy. [2 marks] e) Show the (ABD) matrix [2 marks] Calculate the minimum ultimate reserve factor for the laminate and identify the relevant failure type, using the Max. stress criterion (and show a screen shot of your reserve factor from the software) [4 marks] 9) Calculate the minimum ultimate reserve factor for the laminate and identify the failure type, using the Tsai-Hill failure criterion (and show a screen shot of your reserve factor from the software) [4 marks] h) Compare and explain the analysis results (i.e. reserve factor and failure type) of the two calculations. Note: Use Maximum 50 words. (4 marks] Use the material C-T700 24K" | EP-'E765' in the ELamx database. The properties are: E11 = 129000 MPa X1 = 2553 MPa E2z = 7380 MPa Xc = 1239 MPa 812 = 0.319 Yr = 42 MPa G12 = 4480 MPa Yc = 199 MPa S = 138 MPa