10.1 Consider a honeycomb sandwich panel 20 in. long and 12 in. wide subjected to an in-plane compressive load in the lo

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10 1 Consider A Honeycomb Sandwich Panel 20 In Long And 12 In Wide Subjected To An In Plane Compressive Load In The Lo 1 (53.5 KiB) Viewed 28 times

10.1 Consider a honeycomb sandwich panel 20 in. long and 12 in. wide subjected to an in-plane compressive load in the longer direction of N = - 2000 lb/in. of width. The faces are made of boron/epoxy (V =67%) and the core is aluminum each with the following properties: Boron Epoxy Aluminum Honeycomb Core E = 30.3 x 10ºpsi E = 10.5 x 10 psi E = 2.8 x 100 psi n=0.348 = 0.21 gxy G G = 3.9 x 106 psi G=0.93 x 106 psi = 0.101 lb/in. 3 im 130.074 lb/in. sall362,000 psi If the panel is simply supported on all four edges: a. What is the optimum face stress,,? b. Is the panel overstressed? c. What are the optimum values of each dependent variable (in this case hc, d, t, and t) for the honeycomb construction? t d. If the boron/epoxy ply thickness is 0.0055 in., how many laminates are necessary to approximate the optimum construction? e. What is the weight of the panel per unit planform area?