空间平台与分离式载荷一体化热控设计
doi: 10.11728/cjss2024.02.2023-0041 cstr: 32142.14.cjss2024.02.2023-0041
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吴自帅：男, 1985年5月出生于河南省濮阳市. 现为上海卫星工程研究所热控设计师、高工, 主要研究方向为空间飞行器热控设计和工程研制. E-mail: gentalman.good@163.com
作者简介:
Integrated Thermal Control System for Space Platform and Fractionated Payload
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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.Abstract: 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 platform 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 impact 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 mathematic 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 fractioned payload. The whole figures of the simulations and test results proved the rationality and effectiveness of the system, meanwhile, verified the feasibility of the thermal vacuum test method for the thermal coupled space platform and fractioned payload while would be independent during thermal vacuum test, which can be as a reference of such spacecraft cases.
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Key words:
- Space platform /
- Fractionated /
- Integrated /
- Thermal control
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图 2 空间平台与分离式载荷一体化热控设计方案
Figure 2. Integrated thermal control design of space platform and fractionated payload
图 6 载荷降温速率及共用舱板温度随可开合舱板打开角度的变化
Figure 6. Temperature decent ratio of payload and panel temperature changing with unfold angle of the deployed panel
表 1 试验结果与仿真结果的对比
Table 1. Comparison between experimental results and simulation values
序号 名称 低温环境/℃ 高温环境/℃ 试验值 仿真值(定温) 试验值 仿真值(定温) 1 共用舱板1 –2.7～2.8 0 18.8～23.7 22 2 共用舱板2 –1.3～2.9 0 21.2～29.5 25 3 可开合舱板 –8.5～11.3 –11.6～8.2 –0.1～18.1 –2.1～17.4 4 载荷上半部分 –2.0～7.2 0～6.8 5.2～12.1 7.0～11.8 5 载荷下半部分 –1.7～6.0 –0.8～2.9 13.4～20.1 14.4～20.2 
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表 2 载荷在平台内工作时对平台的影响
Table 2. Effects of payload working to the platform
工况 共用舱板1平均
温度增量/℃共用舱板2平均
温度增量/℃共用舱板向边界
传递热流增量/WT=–30℃, ξ=1.0 4.8 4.7 39.5 T=–20℃, ξ=0.3 9.0 8.9 16.1 T=–20℃, ξ=1.0 4.7 4.4 37.4 T=0℃, ξ=0.1 18.3 18.2 21.3 T=0℃, ξ=1.0 4.9 4.9 49.6 T=10℃, ξ=1.0 4.8 4.9 46.7
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