宇航学报 ›› 2022, Vol. 43 ›› Issue (6): 820-829.doi: 10.3873/j.issn.1000-1328.2022.06.013

• 推进技术与动力 • 上一篇    下一篇

月球探测器着陆过程羽流热效应数值模拟研究

张熇,吴成赓,刘立辉,孙洁,贺碧蛟,蔡国飙   

  1. 1. 北京航空航天大学宇航学院,北京 102206;2. 北京空间飞行器总体设计部,北京 100094;3. 探月与航天工程中心,北京 100086
  • 收稿日期:2022-03-09 修回日期:2022-05-07 出版日期:2022-06-15 发布日期:2022-06-15

Numerical Simulation of Plume Thermal Effects during Lunar Probe Landing

ZHANG He, WU Chenggeng, LIU Lihui, SUN Jie, HE Bijiao, CAI Guobiao   

  1. 1. School of Astronautics, Beihang University, Beijing 102206, China; 
    2. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China; 
    3. Lunar Exploration and Space Engineering Center, Beijing 100086, China
  • Received:2022-03-09 Revised:2022-05-07 Online:2022-06-15 Published:2022-06-15

摘要: 考虑到月球探测器着陆过程变推力发动机工作可能引发羽流热效应,通过差分求解N S方程与直接模拟蒙特卡洛(DSMC)耦合的方法,针对探测器变推力发动机羽流的连续流区与稀薄流区进行了数值模拟,获得了着陆过程不同状态探测器表面的羽流气动热流密度分布,分析了探测器在不同高度及坡度受到的羽流热效应,研究了探测器因落月惯性与发动机延时拖尾等特殊工况羽流气动热的影响程度。数值模拟结果表明,探测器受到的羽流气动热影响总体随着发动机出口与月面间距离减小而急剧增强,随着距离减小至0.434 m,热流密度最大值为429 kW/m 2 ,而且月面坡度对羽流热效应有减弱作用。研究结果可为探测器关机策略的制定提供支撑,为探测器关键部位的热防护提供输入,为探测器整体的设计优化提供服务。

关键词: 月球探测器, 着陆过程, 真空羽流, 羽流热效应

Abstract: Considering that the thermal effects of the vacuum plumes may be induced by the variable thrust engine during the landing process of the lunar probes, the method of coupling the differential solution of the N S equation and the direct simulation Monte Carlo (DSMC) are used to solve the continuous flow region and the rarefied flow of the plume field. The plume aerodynamic heat flux distributions on the surface of the probe at different states during the landing process are obtained, and the thermal effects of the plume on the probe at different heights and slopes are analyzed. The influence of the plume on the probe due to the special conditions such as the inertia when falling on the moon and the delayed tailing of the engine is studied. The numerical simulation results show that the aerodynamic thermal effect of the plume on the probe increases sharply with the decrease of the distance between the engine outlet and the lunar surface. As the distance decreases to 0.434 m, the maximum heat flux is 429 kW/m 2. The slope of the lunar surface weakens the thermal effects of the plume. The research results can provide support for the formulation of the probe shutdown strategy, input for the thermal protection of crucial parts of the probe and services for the overall design optimization of the probe.

Key words: Lunar probe, Landing process, Vacuum plume, Plume thermal effect

中图分类号: