一种卫星推进分系统热控的优化设计方法

An Optimization Design Method for Thermal Control of Satellite Propulsion Subsystem

根据传统卫星推进分系统热控要求,针对推进舱内肼管路及部件进行加热带缠绕和多层隔热组件包覆的问题,提出了一种基于新型推进剂条件下的推进分系统热控优化设计,即取消推进舱内热控处理措施,而是在推进舱的外侧板包覆多层隔热组件,并采用电磁阀补偿加热.对采用优化设计的推进分系统热控设计进行了热平衡试验和在轨验证.结果表明,推进分系统的温度水平和功耗要求均满足目前中国对于卫星的热控要求,且优化设计使推进分系统热控具有功耗低、质量小和易于装配的优点,能够结合卫星构型实现分舱操作.

The conventional thermal control requirements of satellite propulsion subsystem are that the pipings and parts of hydrazine tank need tropical winding and multilayer coating. In this paper, an optimization design for thermal control of propulsion subsystem under a new type of propellant is proposed, in which the propulsion module controlled heat treatment measures are cancelled, the propulsion module outer plate is coated with multiplayer insulation components, and compensation heating for electromagnetic valve is adopted. Thermal balance testing and in-orbit validation are conducted for thermal control propulsion subsystem with optimized design. The results show that the level of propulsion subsystem temperatures and power requirements can meet the requirements ofcurrent range of domestic thermal control of satellites. Optimized design of the propulsion subsystem thermal control have the advantages of low power consumption, light weight and easiness of assembly. By combining with the satellite configuration, the subdivision operation can be achieved.