基于航天器动力管路的主动热控控温算法  

Active Thermal Control Algorithm Based on Spacecraft Propulsion Pipeline

作　　者：黄晨 王淑炜 岳晓飞 汪文明 张义超 Huang Chen;Wang Shu-wei;Yue Xiao-fei;Wang Wen-ming;Zhang Yi-chao(Beijing Institute of Astronautical Systems Engineering, Beijing, 100076)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《导弹与航天运载技术》2017年第4期17-20,共4页Missiles and Space Vehicles

摘　　要：主动热控系统是航天器的重要环境保障系统之一。随着航天技术的不断发展,航天器在太空所处工作环境愈加严酷,载荷类型愈加多样,对主动热控的控温精度和控温方式提出了越来越高的要求。基于卫星和运载火箭常见的控温对象动力管路为基本模型,对开关式和比例式控温算法进行仿真验证,通过对仿真结果的对比和讨论解决了应对环境突变的问题,为后续高精度的控温策略方案设计提供理论依据。The active thermal control system is one of the most important environmental protection systems for long-term stable operation of spacecraft.With the development of aerospace industry,the working environment of spacecraft has become more and more severe,and the load type is more varied,so more and more high requirement is put forward to the control precision and temperature control algorithm.This paper presents a research on active thermal control algorithm based on fuel pipeline model.By comparing the results basing bang-bang control algorithm and proportional control algorithm,this paper gives some discussion and theoretical basis for the design of high-precision active thermal control algorithm.It solves the problems of environmental abrupt change.

关 键 词：主动热控控温算法 燃料管道模型 仿真验证 

分 类 号：V433[航空宇航科学与技术—航空宇航推进理论与工程]