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

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8b. Due to symmetry, only one quadrant of the plate need be treated. Two gridworks are represented—a "coarse" mesh of 21 points, and a "fine" mesh of 65 points. Three basic assumptions were employed in the development of quadrilateral plate element stiffness properties for the desired analyses : (1) The assumed stress pattern of Eqs. (19) (σχ = ax + a%y, σν = a3 + ö 4 #, TXy = fl6). (2) The assumed stress pattern of Eqs. (36) (σχ = a1 + a^x9 dy = a 2 + a 5j> T xy = a s — αδχ — a û)- (3) Assumed linear edge displacements (see Eqs.

Using Eq. (33), the entire set of stiffness coefficients for the swept plate under linear edge displacements has been derived in an explicit (algebraic) form. The set is shown in Fig. 5 and will be employed in analyses discussed in Chapter 4, Section B, 5. Argyris has presented an illustrative application of the unit displacement theorem in Ref. 8, where he derived the stiffness matrix for the rectangular plate in direct stress under the assumption of linear edge displacements. There, by observation rather than through an inversion of the pertinent [B] matrix, he was immediately able to establish the necessary equations for stress and strain.

The idealizations included the equivalent plate, (20> the flexural element-torsion cell,<16>17) and the flexural element-triangular plate skin panel· 10 ) representations. Only the latter 47 METHODS OF M A T R I X S T R U C T U R A L ANALYSIS scheme was found to yield accurate predictions with reasonable consistency. Some further evaluations that encompass more than one approach have since been published. Reference 25 considered a wider variety of structural forms, including the stiffened cylinder, but fewer idealizations than Ref.

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