卫星推进系统温度均衡性控制方法研究

Homogeneity of Thermal Control Method for Satellite Propulsion System

关键词:  推进系统  不平衡分布  温度控制  裕度  闭环

Key words:  Propulsion system  Unbalance distribution  Thermal control  Margin  Closed loop

摘要:

卫星推进系统在轨需要进行温度控制，尤其需要对推进系统的贮箱、管路温度进行合理的控制。针对小卫星、微小卫星热控资源紧张的情况，以及当前的热控设计方法在不同温度环境分布的推进系统应用中存在的温度分布不均的情况，提出了一种优化的推进系统热控设计方法。在常规热控设计方法中考虑测温点最小值的同时，考虑了测温点的最大值因素，并根据最小值、最大值与控温区间的关系确定加热回路的开/关关系。采用本方法在整星热平衡试验中对推进系统进行了温度控制验证。试验结果验证了同时考虑控温区间上限和下限的热控设计方法的可行性和合理性。卫星在轨飞行阶段的推进系统参数验证了该温度控制方法能获得更好的推进系统温度分布均匀性，并保证了工作温度区间上限的裕度。

Abstract:

The thermal control of propulsion system should be carried out in the satellite， and especially the temperature of tanks and pipes should be controlled at a logical range.Based on the development instances of the micro-satellites that the thermal control resource is limited， and that the conventional thermal control method leads the propulsion system’s unbalanced temperature distribution， an optimized thermal control method for propulsion system is proposed for the different temperature environment. In this method， the minimun test value is considered in the conventional thermal control method and the maximun value is also considered， and the condition of heat loop is regarded according to the relationship between the minimun value， maximun value and the control range. This method is applied during the thermal balance testing of satellite， and the results show the feasibility and rationality of this method considering the lower limit and upper limit at the same time. Also， the temperature parameters of on-orbit validation show an evener distribution by this research， which guarantees the upper limit interspace of temperature control range.