HW3_10 Sol - CLARKSON UNIVERSITY Department of Mechanical...

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CLARKSON UNIVERSITY Department of Mechanical and Aeronautical Engineering AE/ME 350 Aircraft Structural Analysis (Fall 2010) Homework #3 Solution Prob 1 . Square Section: Shaded Area (assumed wall thickness = t) Material cross-sectional area, A = (d + t) 2 – (d – t) 2 = 0.01d 2 d 2 + t 2 + 2dt – (d 2 + t 2 – 2dt) = 0.01d 2 4dt = 0.01d 2 t = 0.0025d T = 2 A q = 2d 2 q Since A = d 2 , q = T/(2d 2 ) 4 2 2 0025 . 0 0025 . 0 4 2 2 1 2 1 Gd T d d d T G d t qds AG Torsional rigidity 4 4 0025 . 0 0025 . 0 Gd Gd T T T Circular Section: Assumed wall thickness = t 1
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Material cross-sectional area, A= shaded area = 2 2 2 01 . 0 2 2 2 2 d t d t d dt = 0.01d 2 , t = 0.01d/ q = q d 4 2 2 , q = 2 2 d T T = 2 A 24 2 12 4 0.01 0.01 2 4 Td T dd G d G d      4 4 0.0025 4 0.01 TT Gd T Gd  Torsional rigidities are equal. Prob 2. T = 1000 in-lb T = 2A 1 q 1 + 2A 2 q 2 + 2A 3 q 3   3 2 1 2 5 . 1 2 2 5 . 1 2 2 2 1 2 1000 q q q
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This note was uploaded on 09/30/2010 for the course AE AE 350 taught by Professor Rha during the Fall '10 term at Clarkson University .

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HW3_10 Sol - CLARKSON UNIVERSITY Department of Mechanical...

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