Design and research of integrated components for microsatellite thermal control system

Abstract With the increasing development of aerospace technology, micro satellites have attracted high attention in field due to their advantages such as short cycle, low system investment, and flexible launch methods. Their level internal equipment integration, heat flux density, complex uncertain working modes pose new challenges thermal control design. At present, design still mainly adopts passive methods, while active has been widely used fluid circuit large spacecraft, mostly “task oriented mode”. Its cost, long poor adaptability other characteristics cannot be applied methods satellites. In response problems brought by power density inertia microsatellites design, this paper proposes an loop suitable for microsatellites. addition cold plate radiator at end, forms integrated component form a shared substrate. The miniaturization, lightweight, rapid replacement board card. Through simulation technical analysis key components, We believe that scheme is reasonable feasible, providing subsequent