摘要
针对降低返回系统质量与提高有效载荷的日益需求,一种新型充气式再入减速器成为国际上研究的热点之一。它具有易折叠包装、质量轻、展开阻力面积大、再入时弹道系数低和产生的气动热量小等明显优点,为航天员应急返回、深空探测以及有效载荷的回收提供了一种新的技术途径。文章针对单充气环薄膜型减速器再入时的气动特性,对其外围流场进行了仿真分析,对比分析了充气式减速器不同锥角及阻力面形状对气动特性的影响,结果表明,减速器所受的气动阻力与其锥角有明显关系,且具有非线性特点,当减速器锥角保持不变时,其阻力面的形状对气动阻力也有一定影响,且减速器再入过程中的阻力面形状可以改变其压力分布。文章最后给出了充气减速器外围的流场、温度场和压力场,以及它们的变化特征,这能为充气式减速器的结构设计提供一定的参考依据。
With the growing demand for reduction of Re-entry system mass and increase of pag load, more researchers give focus on a new type of inflatable membrane aeroshell （IMA）, which is of easy packaging, light mass and large drag area. This aeroshell has low ballistic coefficient and aerodynamic heat. It provides a new technical approach for emergency re-entry of astronauts, exploration of space and recovery of payloads. In connection with the problem of aerodynamic characteristics of the aeroshell, the flow fields are analyzed in this paper. Moreover, the aeroshell＇s aerodynamic characteristics at different cone angles and with different shapes of drag surface are compared. These results show that IMA＇s aerodynamic characteristics are closely connected with cone angle and their relationship is non-linear. When cone angle is the same, IMA＇s drag has a relation with drag surface＇s shape as well. Finally, its velocity, temperature and pressure field of IMA are provided. The research can provide some references for structural design of IMA.
出处
《航天返回与遥感》
2013年第3期49-55,共7页
Spacecraft Recovery & Remote Sensing
基金
中央高校基本科研业务费专项资金资助(编号:HIT.NSRIF.2013032)
关键词
减速器
充气环
薄膜型
气动特性
aeroshell
inflatable loop
membrane
aerodynamic characteristics
