Thermal Design and Analysis of Spacecraft During Flight Missions
Thermal control system (TCS) is one of the main systems in spacecraft, which guarantees the assigned thermal conditions of all subsystems and equipment during spacecraft (SC) lifetime, and partially participation in ground thermo-stating during testing. TCS is designed according to the calculation of SC thermal budget to estimate device panels’ ability for dissipation excess heat, which is emitted by SC equipment in process of nominal operation during maximum external heat flux. Calculating radiation surface areas of equipment panels is performed to reject heat dissipation. Estimating of SC panels cooling capacity during minimum external heat fluxes is required to calculate power of heaters. SC model in Low Earth Orbit (LEO) is created by thermal desktop program, in order to launch a parametric study of the variable space parameters which would effect on SC at the LEO.