By J. N. Reddy (auth.), Carlos A. Mota Soares, Cristóvão M. Mota Soares, Manuel J. M. Freitas (eds.)
A compact presentation of the principles, present cutting-edge, contemporary advancements and learn instructions of all crucial innovations on the topic of the mechanics of composite fabrics and constructions. distinct emphasis is put on vintage and lately constructed theories of composite laminated beams, plates and shells, micromechanics, influence and harm research, mechanics of fabric structural composites, excessive pressure fee checking out and non-destructive trying out of composite fabrics and buildings. themes of transforming into value are addressed, reminiscent of: numerical tools and optimisation, id and harm tracking. the most recent effects are offered at the artwork of modelling shrewdpermanent composites, optimum layout with complex fabrics, and commercial functions. every one portion of the booklet is written by way of the world over known specialists who've committed so much in their study paintings to a selected box.
Readership: Postgraduate scholars, researchers and engineers within the box of composites. Undergraduate scholars will enjoy the therapy of the rules of the mechanics of composite fabrics and structures.
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Extra resources for Mechanics of Composite Materials and Structures
10 al ~ ..... 2 Figure 4· 6. ,,,,,, versus plate thickness for simply supported cross-ply laminates under sinusoidal load (CLPT). 50 ~ ........ 7. Maximum shear stress (iTxz) from equilibrium versus plate thickness (zjh) for simply supported cross-ply laminates under sinusoidal load (CLPT). 21 The effect of shear deformation on deflections and stresses is discussed next. 9 show the maximum nondimensionalized deflections w = wo(E2 h 3 /b 4 qo) of simply supported, square, symmetric and antisymmetric laminates under sinusoidally distributed load (SSL) and uniformly distributed load (UDL), for different side-to-thickness ratios.
For linear analysis, we set N = 0 and P = 0, in addition to setting the nonlinear terms in the strain-displacement equations to zero. 25) where Aij are called extensional stiffnesses, Dij the bending stiffnesses, and Bij the bending-extensional coupling stiffnesses, which are defined in terms of the lamina stiffnesses Q~7) as 13 Dij = 1 ~ -(k) 3 3" L.. 26) k=l Note that (j's, and therefore A's, B's, and D's, are, in general, functions of position (x, y). , moisture) effects. 3. , the transverse normals do not remain perpendicular to the midsurface after deformation.
When the plate in-plane characteristic dimension to thickness ratio is on the order 50 or greater, the rotation functions 4>x and 4>y should approach the respective slopes of the transverse deflection: A. __ 'Px - 8wo A. &. hi. 2 8x 2 8y 8x ~+1(~)2 8y =1 ~+4>. hi. 33b) 8Qx 8Qy N _ J, 8 2wo 8x + By + + q - 0 8t2 8Mxy _ Q _ J. 8 24>x 8y x - 2 8t2 8Mxy 8Myy _ Q _ J. 33e) where the force and moment resultants are the same as defined in Eq. 35) k=l and K denotes the shear correction factor, which is introduced to account for the discrepancy between the actual shear forces and those due to the constant stress state predicted by the first-order theory.