中国空间科学技术

中国空间科学技术 ›› 2019, Vol. 39 ›› Issue (6): 80-.doi: 10.16708/j.cnki.1000-758X.2019.0053

• 技术交流 • 上一篇    下一篇

空间再入充气系统的大攻角气动及结构仿真研究

张章，吴杰，王立武，侯安平，曹旭，王奇   

  1. 1. 北京空间机电研究所 中国空间技术研究院航天器无损着陆技术核心专业实验室，北京100094
    2. 北京航空航天大学 能源与动力工程学院 航空发动机气动热力国家级重点实验室，北京100191
  • 出版日期:2019-12-25 发布日期:2019-12-06

Aerodynamic and structural simulation of space reentry inflatable aeroshell at high angle of attack

ZHANG Zhang, WU Jie, WANG Liwu, HOU Anping， CAO Xu， WANG Qi   

  1. 1. Key Laboratory for Nondestructive Spacecraft Landing Technology of CAST, Beijing Institute of Space
    Mechanics & Electricity, Beijing 100094，China
     2. National Key Laboratory of Science and Technology on AeroEngines AeroThermodynamics，School of Energy and
    Power Engineering，Beihang University, Beijing 100191，China
  • Published:2019-12-25 Online:2019-12-06

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摘要： 为描述空间再入充气系统在大攻角状态下的气动力与结构特性，利用CFD模型研究了不同攻角下的流场分布及气动力系数变化。同时建立了考虑内充压作用的有限元模型，并以高超声速流场作为输入，采用流固单向耦合的方法分析了不同攻角下的气动力对结构静力学特性的影响。研究表明：随攻角的增大，轴向力系数呈整体下降趋势，而法向力系数及俯仰力矩系数分别呈M型及W型变化趋势；此外，随着攻角的增加，结构最大应力整体呈上升趋势，并在45°攻角附近增幅最大。

关键词: 空间再入充气系统, 高超声速流场, 流固单向耦合, 静力学特性

Abstract: For the description of the aerodynamic and structural characteristics of the space reentry inflatable aeroshell at high angle of attack, the CFD model was used to calculate the flow field distribution and aerodynamic coefficients at different angles of attack. At the same time, the finite element model considering the internal pressure was established. Using the hypersonic flow field as the input, the influence of aerodynamic force on the static characteristics of structure at different angles of attack was analyzed by the one way fluidstructure interaction method. The results show that with the increase of angle of attack, the axial force coefficient decreases as a whole, while the normal force coefficient and pitching moment coefficient show Mtype and Wtype trends. Furthermore, the maximum stress of the structure increases with angles of attack increment, and the maximum increase is near 45° angle of attack.

Key words: reentry inflatable aeroshel, hypersonic flow, one way fluidstructure interaction, static stress characteristics