m17_ps05_spring04

m17_ps05_spring04 - gust loading etc. The three critical...

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Unified Engineering Spring 2004 Problem M17 An aircraft wing structure is being designed. You are responsible for "sizing" a rectangular panel of the wing skin (in this case sizing means specifying the thickness). The material to be used is Aluminum 7075 T6, which has a uniaxial yield stress of 500 MPa. The loading is specified in terms of line forces (i.e. forces per unit length in the x-y plane), N x , N y , S , where N x and N y are tensile line forces and S xy is the shear loading. These line forces are xy derived from the estimated design loads on the airframe due to different flight conditions,
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Unformatted text preview: gust loading etc. The three critical load cases for this component are thought to be: Load case N x (kN/m) N y S xy 1 +250 -500 +200 2 +300 +500 -400 3 +600 -300 0 Calculate the required thickness of the wing skin for this component so that it will survive all three loading conditions. Assume that the material obeys Von Mises Yield criterion, assume that the out of plane (z direction) loading is negligible) and apply a factor of safety of 1.5 to your results....
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.

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