Matrix Methods of Structural AnalysisB. Fraeijs de Veubeke on behalf of Advisory Group for Aeronautical Research and Development, North Atlantic Treaty Organization, 1964 - Airplanes - 343 pages |
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Page 37
... effect is , no doubt , due to coupling with the longi- tudinal direct stresses in the cover . However , the magnitude of the bending stresses on the outside is much less and the most important ring stresses — which can be at least as ...
... effect is , no doubt , due to coupling with the longi- tudinal direct stresses in the cover . However , the magnitude of the bending stresses on the outside is much less and the most important ring stresses — which can be at least as ...
Page 106
... effects are valid . Just as in Section C.f our large displacement approach includes the effect of the change of geometry on the equilibrium conditions and yields in the limit , for infinitesimal displacements , the initial buckling ...
... effects are valid . Just as in Section C.f our large displacement approach includes the effect of the change of geometry on the equilibrium conditions and yields in the limit , for infinitesimal displacements , the initial buckling ...
Page 298
... effect of the large scaling error on deflexions is seen to be very small and that of the root bay consistency error is negligible . A larger effect is seen to result from the tip bay consistency error indicating a high magnification of ...
... effect of the large scaling error on deflexions is seen to be very small and that of the root bay consistency error is negligible . A larger effect is seen to result from the tip bay consistency error indicating a high magnification of ...
Contents
A PRÉCIS OF RECENT DEVELOPMENTS | 3 |
MATRIX FORCE METHOD IN NONLINEAR PROBLEMS | 9 |
A FORCE METHOD | 10 |
Copyright | |
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Appendix applied approximate Argyris assumed axes b₁ basic beam bending bending moment boundary buckling calculated coefficients complete complex structure components corresponding cross-section cut-out deflexions deformations derived determined direct stresses direction cosines displacement method displacement vector Douglas Aircraft Company effect elastic equations equilibrium conditions experimental external loads flange load flexibility matrix fuselage geometrical given grid hence incremental initial strains introduce iteration kg/cm² kinematic lb/in² linear modes nodal displacements nodal forces nodal points node non-linear obtained parallelogram plane plastic Poisson's ratio problem procedure programme quadrilateral rectangular redundancies rings self-straining shear flow shear strain shear stress shown in Fig skin small deflexion solution spar spar element statically statically determinate stiffness matrix stiffness method stress distribution stress matrix stringers structural analysis structural idealization symmetrical taper technique theory tion triangle triangular elements Turner unit displacement values vector vertices wing yields zero Δω