外热流扰动下航天器精密控温系统的设计及参数优化  

Design and Parameter Optimization of High-precision Temperature Control System for Spacecraft Disturbed by External Heat Flux

作　　者：耿利寅[1] 张传强 童叶龙[1] 韩东阳 孟恒辉[1] 彭方汉[1] GENG Liyin;ZHANG Chuanqiang;TONG Yelong;HAN Dongyang;MENG Henghui;PENG Fanghan(National Key Laboratory of Spacecraft Thermal Control,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航天器热控全国重点实验室,北京100094

出　　处：《航天器工程》2023年第6期10-17,共8页Spacecraft Engineering

摘　　要：对于航天器精密控温系统,外热流的周期性波动是影响被控对象温度稳定性的主要扰动来源。文章以一个典型的航天器精密控温系统为研究对象,建立了融合空间外热流扰动、系统热设计状态和控温算法的系统统一数学模型。经简化实现模型的线性化后,采用频率响应法对系统进行分析,获得了系统稳态输出的理论解。文章从航天器热控设计实际出发,分析了各热物理参数和控制参数对系统输出温度稳定性的影响,提出了以降低外热流扰动引起的温度波动为目标的热设计和控温参数优化原则和方向。文章还以海洋盐度探测卫星综合孔径辐射计天线接收机的高稳定度控温设计为实例,展示了按照上述优化原则和思路调整热控措施和控温参数,经仿真计算对比不同参数的输出效果,最终获得理想控温效果的过程。该实例验证了文章理论解和优化设计指导思路的正确有效性。For a precision temperature control system of spacecraft,the periodic fluctuation of external heat flux is the main disturbance source that affects the output temperature stability of the controlled object.In this paper,a unified mathematical model integrating heat flux,thermal design state,and control algorithm of the system is established based on a typical spacecraft temperature control system.After simplifying the linearization of the model,the frequency response method is used to analyze the system and obtain the theoretical solution of steady state.Starting from the actual thermal control design of spacecraft,this paper analyzes the influence of various thermal and control parameters on the output temperature stability of the system and proposes the optimization principles and directions of thermal design and control parameters with the goal of reducing temperature fluctuations caused by heat flux disturbances.This paper also takes the high stability temperature control design of a certain type of synthetic aperture radiometer antenna receiver as an example,illustrating the process of adjusting the control parameters according to the above optimization principles and ideas,comparing the output effects under different parameters through simulation calculations,and finally obtaining the ideal temperature control effect.This example verifies the correctness and effectiveness of the theoretical solution and optimization design guidance in this paper.

关 键 词：航天器热控 精密控温 外热流扰动 温度稳定性 比例积分控温 参数优化 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]