宇航学报

宇航学报 ›› 2017, Vol. 38 ›› Issue (3): 230-239.doi: 10.3873/j.issn.1000-1328.2017.03.002

• 综述 • 上一篇    下一篇

火星进入器高超声速气动力/热研究综述

唐伟，杨肖峰，桂业伟，杜雁霞   

  1. 中国空气动力研究与发展中心空气动力学国家重点实验室，绵阳 621000
  • 收稿日期:2016-08-12 修回日期:2017-01-03 出版日期:2017-03-15 发布日期:2017-03-25
  • 基金资助:

    国家自然科学基金（11472295,51308531）

Review of Hypersonic Aerodynamics and Aerothermodynamics for Mars Entries

TANG Wei, YANG Xiao feng, GUI Ye wei, DU Yan xia   

  1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2016-08-12 Revised:2017-01-03 Online:2017-03-15 Published:2017-03-25

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摘要：

针对火星探测任务进入阶段复杂且特殊的气动力/热环境，总结了国际火星探测进入任务的历史沿革、发展动向和关键气动问题，综述了火星进入器地面风洞试验、飞行任务和高超声速气动力/热数值模拟的研究进展，提出了国内后续研究的重点方向，包括复杂气动问题建模和精细化模拟、风洞及相关试验研究、气动设计相关问题等，为我国未来火星进入器设计提供技术支持。

关键词: 火星进入器, 高超声速, 气动力, 气动热, 数值模拟, 风洞试验

Abstract:

The history and new trend of Mars exploration missions and the essential characteristics of aerodynamics and aerothermodynamics for Mars entries are summarized in the present article. The state-of-the-art research of ground experiments, flight testing and numerical techniques for hypersonic Martian aerodynamics/aerothermodynamics prediction are reviewed in detail. The potential work, including the complicated aerodynamics/aerothermodynamics modeling and simulation, further wind tunnel experiments, and aerodynamic design issues is conclusively proposed for future Mars entry capsule design.

Key words: Mars entry capsules, Hypersonic, Aerodynamics, Aerothermodynamics, Numerical simulation, Wind tunnel experiment

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