Morteza Shahravi - Department of Aerospace Eng.
Sina Falahzade - department of SGC
Madhid Mokhtari - S.G. center of research

In the present paper, an analytical approach is used to study the thermal deflections of a simply supported composite plate with a beam-like stiffener. The results for a plate–beam system exposed to a sinusoidal thermal load is used to study the effects of the low Earth orbit (LEO) thermal conditions on the composite plates, which have been used in the structure of satellites and spacecraft. To solve the governing equations of the system, the Laplace transform method for the time domain is used with the Navier series expansions. As the employed method is completely analytical, the results are exact.

Ribbed composite plate, Thermoelastic Bending, Laplace transform, Advanced composite