摘要
返回器气动特性研究对宇宙飞船的研制起着先导和制约作用。文章对Apollo、CEV和类Soyuz这3种典型的轴对称钝头体再入返回器气动布局进行了气动特性的对比分析,发现与Apollo、CEV相比,类Soyuz外形的升阻比偏小,无法满足以第二宇宙速度载人空间再入返回的要求。在此基础上研究了几何参数(包括倒锥角和球冠半径)变化对类Soyuz外形返回器气动性能的影响规律,从中得到类Soyuz外形的改进方向,提出了一种以类Soyuz外形为基础的改进设计外形,并对该外形的升阻特性、稳定性和配平特性等相关气动特性进行了分析。研究表明通过对几何外形参数的调整优化来提高类Soyuz外形的升阻比,从而达到以第二宇宙速度再入返回的升阻比要求,这样的技术途径是可行的。
The aerodynamic characteristics investigation of reentry capsule plays an important role in the design of spacecraft. Comparative analysis of the aerodynamics between Soyuz and Apollo/CEV configurations is accomplished in this paper. The lift-to-drag ratio of Soyuz which is lower than that of Apollo/CEV cannot meet the requirement of manned capsule reentry at second cosmic velocity from space. The influence of geo- metric parameters, including after-body angle and heat shield radius, on the aerodynamic characteristics of Soyuz configuration is analyzed. And a modified configuration is suggested on the basis of Soyuz. The aerody- namic characteristics of the modified configuration are analyzed, including lift-to-drag ratio, stability, and trim characteristics. The results show that adjusting and optimizing the geometric parameters of Soyuz re-entry capsule is a feasible way for designing a capsule configuration to meet the high lift-to-drag ratio requirement of manned capsule reentry at second cosmic velocity.
出处
《航天返回与遥感》
2013年第6期11-20,共10页
Spacecraft Recovery & Remote Sensing
基金
国家自然科学基金(90916001)
关键词
再入返回器
气动布局
气动特性
数值计算
reentry capsule
aerodynamic configuration
aerodynamic characteristics
numerical simulation
