Abstract
Composite plates’ subjected to sudden surface heating is investigated. Simply supported boundary conditions along the four sides of the plat are considered. The effect of plate thickness and stacking sequence on the maximum deflection that is induced by the thermal heat flux for a graphite-epoxy composite plate is studied using finite element analysis. Symmetric angle ply laminates plate shows least deformation compared the other stacks of the same thickness.
Highlights
Spacecraft usually has large and flexible appendages that carry solar arrays which are connected to its main platform
The effect of plate thickness and stacking sequence on the maximum deflection that is induced by the thermal heat flux for a graphite-epoxy composite plate is studied using finite element analysis
Such a consideration is acceptable since the first mode shape is the most dominant one, and since we are interested only in the maximum displacement
Summary
Spacecraft usually has large and flexible appendages that carry solar arrays which are connected to its main platform. (Eslami & Maerz, 1995) published an exact solution for the thermally induced vibrations of a cross-ply laminated plate by hygrothermal effects using the CLT This solution is obtained by considering the total deflection as the superposition of the quasi-static and dynamic deflections. (Li, Xiang, Chen, & Xue, 2007) studied the thermally induced nonlinear vibration of practical thin-walled large-scale space structures subjected to suddenly applied thermal loading and analyzed using the finite element method They found that in the coupled thermal-dynamic system, the stability property of the system depends on only the heat incident angle vector and damping ratios. (Gupta & Singhal, 2010) studied the effect of non-homogeneity on thermally induced vibration of orthotropic visco-elastic rectangular plate of linearly varying thickness They developed an analytical model using the separation of variables method, to solve the governing differential equation. This study is made more general in that it covers laminates of more than one lamina (effect of thickness within thin plate limits), various types of laminates (unidirectional-ply, cross-ply and angled-ply), and laminates with symmetric and anti-symmetric stacking
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