چكيده به لاتين
Satellite thermal analysis is one of the topics that receive special attention in the space industry today. Various active and inactive methods are used for thermal control of satellites and satellite carriers to ensure the safety of equipment at all stages of the mission. In this research, a satellite is designed as a problem by modeling the sent satellites and then examines the types of fluxes entering the satellite from the pre-launch stage to its orbit and the amount of these thermal fluxes and their impact on the components. The structure is discussed. Also, various types of satellite heat control equipment have been introduced and how they work and its advantages and disadvantages have been studied. In the continuation of this study, the thermal modes of the satellite during launch and further investigation of molecular heating during launch and the effects of aerodynamic force on multi-layer satellite insulators and the possibility of rupture of these insulators and subsequent consequences in the moments after separation of the satellite aerodynamic cap. Paid. In the selected satellite, the camera is located on the upper surface of the satellite, so the top of the satellite, imaging equipment and multi-layer insulation are affected by heating and aerodynamic force from free molecules. To prevent these destructive effects, the satellite was modeled using Abacus software and simulated with finite element solution method. Calculations related to heating and effective power are calculated by MATLAB software. The result of these calculations led to the determination of the optimal separation height of the aerodynamic cap. The minimum allowable height for separation of the warhead in terms of heating is 95 km from the ground, which has been determined by considering the reliability coefficient and aerodynamic force on the insulation at a height of 100 km, safe and optimal points for this stage of satellite launch.
