宇航学报

宇航学报 ›› 2019, Vol. 40 ›› Issue (9): 1095-1102.doi: 10.3873/j.issn.1000-1328.2019.09.014

• 空间科学 • 上一篇    

月球着陆器两相流体回路性能衰退分析与验证

王录，苗建印，张红星，张有为，陈建新   

  1. 1. 北京空间飞行器总体设计部，北京 100194；2. 空间热控技术北京市重点实验室，北京 100094
  • 收稿日期:2018-12-03 修回日期:2019-03-02 出版日期:2019-09-15 发布日期:2019-09-25
  • 基金资助:

    中国月球探测科技专项工程

Analysis and Validation of Performance Degradation of Two Phase Fluid Loop in a Lunar Lander

WANG Lu, MIAO Jian yin, ZHANG Hong xing, ZHANG You wei, CHEN Jian xin   

  1. 1. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China; 2. Beijing Key Laboratory of Space Thermal Control, Beijing 100094, China
  • Received:2018-12-03 Revised:2019-03-02 Online:2019-09-15 Published:2019-09-25

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摘要：

针对嫦娥三号着陆器两相流体回路12个月球昼夜的寿命需求，开展了氨分解导致两相流体回路传热温差增量的分析和试验验证，结果表明寿命末期不凝气体引起传热温差增量不超过2.2 ℃，同位素核热源(RHU)向探测器的供热量减小0.6 W，设备温度整体降低0.6 ℃，对热控系统影响可忽略。根据在轨遥测，寿命周期内，两相流体回路工作在45 ℃~50 ℃时不凝气体引起的传热温差增量不超过1.5 ℃，与地面验证结果吻合较好；经历52个月球昼夜周期内，传热温差在3.5 ℃~4.7 ℃内波动，在轨工作良好。

关键词: 月球着陆器, 重力驱动两相流体回路, 性能衰退, 不凝气体

Abstract:

The increment of the heat transfer temperature difference of the two-phase fluid loop of the Chang’E-3 lander caused by the non-condensable gas is analyzed and tested for the one-year lifetime demand (12 Moon days and nights). The results reveal that at the end of the one-year lifetime, the increment of the heat transfer temperature difference caused by the non-condensable gas is 2.2 ℃. It reduces the heat supply from the radioisotope heating unit (RHU) to the lander by 0.6W and the temperature of the equipment is reduced by 0.6 ℃. It can be ignored for the thermal control system. According to the telemetry data, during the period of 12 Moon days and nights, when the two-phase fluid loop works in the range of 45 ℃~50 ℃, the increment of the heat transfer temperature difference caused by the non-condensable gas is less than 1.5 ℃,which is in good agreement with the results of the ground analysis and verification. During the period of 52 Moon days and nights, the heat transfer temperature difference fluctuates in the range 3.5 ℃~ 4.7 ℃ , there is no increasing trend, the two-phase fluid loop works well on orbit.

Key words: Lunar lander, Gravity-driven two-phase fluid loop, Performance degradation, Non-condensable gas

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