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By Richard H Gallagher; Rattinger Ivan.; John S Archer; North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development. Structures and Materials Panel

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Additional info for A correlation study of methods of matrix structural analysis : report to the 14th Meeting, Paris, France, July 6, 1962

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75 x 106 psi, μ = 1/3 2. Test Results The models were tested for displacements by clamping them along the 2 in. wide root support and simultaneously applying load to the two corresponding spar-rib intersection points on opposite semispans. The measured load-displacement data was operated upon, using procedures detailed in Ref. 5, to yield a set of displacement influence coefficients for each wing. The resulting sets of values for Models 1, 3, 4 and 5 are presented in Tables 1 and 2 (end of chapter).

In assuming the wing to be a variable thickness plate, the usual approach is to establish an equivalent flexural rigidity per unit width from the combined properties of the skin and internal members, this value being constant within each area defined by the planform gridwork of reference points. e. vertical shear deformation would be disregarded. Analyses of the subject wing models have been performed in this manner and reported in Ref. 7 ; vertical shear deflection effects were approximated. *3) In general, these formulations are not those of an equivalent plate idealization but do approach the latter under special circumstances.

IL s a r s s r a a m . _ - u PLANFORM I! 0^0" sheet. > o Γ3 q Π^ ' UÜ U) J1 r > > d Ω H H H > o 1/3 W H M O ö Model material - 606I-T6 Aluminum. 040" sheet. For internal structure across 1" support width, see details of Model 2 (Figure II). SECTION A-A 53 Fig. 13. Model 5—Geometry and details. 00 in. 50 in. wide flanges. The central spar of each wing consisted of two such channels, placed back-to-back; all other internal members were single channels. 063 in. thick. 125 in. thick. The skins and internal members were riveted together.

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