空间平台与分离式载荷一体化热控设计  

Integrated Thermal Control System for Space Platform and Fractionated Payload

作　　者：吴自帅[1] 张赪栋 雷智博 翟载腾[1] 姚建[2] WU Zishuai;ZHANG Chengdong;LEI Zhibo;ZHAI Zaiteng;YAO Jian(Laboratory of Space Mechanical and Thermal Integrative Technology,Shanghai Institute of Satellite Engineering,Shanghai 200240;Shanghai Academy of Spaceflight Technology,Shanghai 201109)

机构地区：[1]上海卫星工程研究所空间机热一体化技术实验室,上海200240 [2]上海航天技术研究院,上海201109

出　　处：《空间科学学报》2024年第2期379-385,共7页Chinese Journal of Space Science

摘　　要：随着航天探索需求发展,对组合式航天器通过空间平台在轨完成释放,分离出有效载荷或舱段来实现更复杂功能的需求愈加迫切.空间平台为分离前舱段或载荷提供服务保障.在假设的空间平台和分离式载荷条件下,提出一种空间平台与分离式载荷一体化热控设计,进行热控方案设计,并对载荷存储控温、载荷与平台互相影响、分离时平台温度变化进行热仿真,同时开展初步热真空试验,验证稳态工况下热设计的正确性,并校正热模型以开展更多工况的分析.通过热试验和仿真获得了该设计的温度特性和热量传递特性,数据分析表明该设计合理有效,验证了热耦合的载荷和平台进行独立热试验方法的可行性,可为此类航天器热控制提供依据.With the development of space exploration,combined spacecraft which can implement more complicated targets through fractionated payload or part of the spacecraft separated from the space plat-form have been in urgent need.Space platform provides carriage service for the fractionated payload or part of the spacecraft before separation.Under the hypothetical space platform and fractionated payload conditions,the paper proposed an integrated thermal control system for it,simultaneously,simulations of several cases such as thermal control efficacy for the payload during storage stage,the thermal im-pact between the space platform and the fractionated payload,and the temperature variation of the platform during separation were carried out.Moreover,the steady-state simulations and thermal mathe-matic model were verified through thermal vacuum test.Thermal simulations and thermal vacuum tests generate the scheme characters of the temperature and thermal fluxes between the platform and frac-tioned payload.The whole figures of the simulations and test results proved the rationality and effective-ness of the system,meanwhile,verified the feasibility of the thermal vacuum test method for the ther-mal coupled space platform and fractioned payload while would be independent during thermal vacuum test,which can be as a reference of such spacecraft cases.

关 键 词：空间平台 分离式 一体化 热控 

分 类 号：V1[航空宇航科学与技术—人机与环境工程]