航天器高精度控温系统设计的稳定性条件  

Stability conditions for designing high-precision temperature control system for spacecraft

作　　者：耿利寅[1] 孟恒辉[1] 张传强 彭方汉[1] 童叶龙[1] 韩东阳 GENG Liyin;MENG Henghui;ZHANG Chuanqiang;PENG Fanghan;TONG Yelong;HAN Dongyang(Beijing Key Laboratory of Space Thermal Control Technology,Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部空间热控技术北京市重点实验室,北京100094

出　　处：《航天器环境工程》2023年第2期115-121,共7页Spacecraft Environment Engineering

摘　　要：航天器热控设计中普遍采用时间离散型控温系统,其自身稳定性将影响控温效果,尤其是高精度控温系统的稳定性更直接影响控温精度指标的达成。文章以某典型航天器高精度主动控温系统为研究对象,首先建立融合其热物理模型和控制算法的统一控温系统模型,并结合航天器热控领域的工程实际,通过合理简化实现了模型的线性化;然后基于上述线性化模型,对离散控温系统的稳定性进行研究,应用数学分析及经典控制理论方法对航天器热控设计中实际采用的基于比例和PI算法的控温系统进行理论求解,获得了保持系统稳定的充要条件;最后采用仿真分析的方法验证了上述约束条件的正确性。The internal stability of widely used time-discrete temperature control system in spacecraft thermal control design will affect the temperature control effect.In particular,the stability of high-precision temperature control systems directly affect the achievement of temperature control accuracy.With a typical highprecision active temperature control system of a spacecraft as the research object,a unified temperature control system model that integrated the thermophysical model and control algorithm was established in this paper.And combining the engineering practice in spacecraft thermal control field,the model was linearized by reasonable simplification.Then based on the above linearized model,the stability of discrete temperature control system was studied.The mathematical analysis and classical control theory methods were applied to theoretically solve the temperature control system according to proportional and PI algorithms.The necessary and sufficient conditions for keeping the stability of the system was obtained.Finally,the correctness of the above constraints was verified by simulation analysis.

关 键 词：航天器热控 高精度控温 温度稳定性 统一模型 PI控温 

分 类 号：N945.12[自然科学总论—系统科学] V423.41[航空宇航科学与技术—飞行器设计]