嫦娥五号轻量化泵驱单相流体回路热总线设计及实现

宁献文; 徐侃; 王玉莹; 蒋凡

doi:10.7527/S1000-6893.2021.26292

航空学报 >

2022 , Vol. 43 >Issue 12: 126292 - 126292

DOI: https://doi.org/10.7527/S1000-6893.2021.26292

流体力学与飞行力学

嫦娥五号轻量化泵驱单相流体回路热总线设计及实现

宁献文 ,
徐侃 ,
王玉莹 ,
蒋凡

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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

收稿日期: 2021-08-30

修回日期: 2021-09-05

网络出版日期: 2021-10-09

基金资助

国家自然科学基金（11472040）

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Chang'e-5 complex of lander and ascent vehicle lightweight pumped fluid loop thermal bus: Design and implementation

NING Xianwen ,
XU Kan ,
WANG Yuying ,
JIANG Fan

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Beijing Key Laboratory of Space Thermal Control Technology, Beijing Institute of Spacecraft System Engineering (ISSE), Beijing 100094, China

Received date: 2021-08-30

Revised date: 2021-09-05

Online published: 2021-10-09

Supported by

National Natural Science Foundation of China(11472040)

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摘要

针对嫦娥五号着陆上升组合体月面无人自动采样任务中面临的热控难题，提出一种轻量化泵驱单相流体回路热总线及设计方法，通过热总线将结构板式固定辐射散热面、消耗型散热装置高温水升华器构建为一套组合式热沉，实现了探测器组合体能量的一体化调度管理与在轨分离重构，热总线系统干重15 kg，占热控系统重量的比例在20%以下。在轨飞行结果表明：轻量化泵驱单相流体回路热总线工作正常，管路沿程温差小于7℃，热排散能力达30 W/kg。上升器月面起飞前热总线分离重构过程中工质排放压力变化曲线与地面实验结果一致。流体回路热总线在轨各项性能指标均符合设计预期，验证了轻量化泵驱单相流体回路热总线技术的合理性与可行性，亦可为其他类型航天器热控设计提供参考。

关键词： 嫦娥五号; 热控; 热总线; 流体回路; 水升华器

本文引用格式

宁献文 , 徐侃 , 王玉莹 , 蒋凡 . 嫦娥五号轻量化泵驱单相流体回路热总线设计及实现[J]. 航空学报, 2022 , 43(12) : 126292 -126292 . DOI: 10.7527/S1000-6893.2021.26292

Abstract

In view of the thermal control problem faced in lunar robotic sampling mission of Chang'e-5 complex of lander and ascent vehicle, a lightweight pumped fluid loop thermal bus and design method were proposed. Through the thermal bus, the "structural plate fixed radiator + high temperature water sublimator" was jointly constructed as a set of combined heat sink to realize the integrated thermal management of the probe energy and the separation and reconstruction. The dry weight of pumped fluid loop is 15 kg, accounting for less than 20% of the weight of the thermal system. The on-orbit flight data show that the lightweight pumped fluid loop thermal bus works normally, the maximum temperature difference of thermal bus is no more than 7℃, and the heat dissipation capacity is 30 W/kg. The pressure variation curve of working medium venting in the process of the thermal bus separation and reconstruction before ascent vehicle take-off is consistent with the ground experimental results. All performance indexes of the pumped fluid loop on-orbit meet the design expectations, which verify the rationality and feasibility of the lightweight pumped fluid loop thermal bus technology, and can also provide some reference for the thermal control design of other types of spacecraft.

Key words： Chang'e-5; thermal control; thermal bus; fluid loop; water sublimator

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