Analysis of transient temperature field of the laminate composite membrane in space environment

The on-orbit transient temperature of reflector laminate film was analyzed by using finite element method (FEM). Numerical simulation was used by FEM software ANSYS. Results reveal that the temperature levels of the laminate composite membrane alternate greatly in the orbital period, which is about ±80°C. This range exceeds the material's operating temperature level. So it is necessary to put effective thermal control into effect to the laminate composite membrane. There is temperature gradient in the thickness direction of the laminate composite membrane; there is a light change in Kevlar/Epoxy layer. The temperature of the laminate composite membrane is obviously lower than the seam's temperature. Results provide reference to the thermal control of the inflatable reflector with high precision requirement.