充气式再入航天器总体方案及关键技术初探

摘要

Inflatable re-entry vehicle is a new re-entry spacecraft, with outstanding performance of simple system, low-mass, low-aerodynamic heating and fitting in different shapes of payload. It’s suitable for atmos-pheric re-entry in human space flight and planetary exploration missions. This paper introduces the develop-ment of inflatable re-entry vehicle at home and abroad, and studies the general scheme. By consulting to the Russian inflatable re-entry and descent technology (IRDT) design, a configuration scheme of inflatable re-entry vehicle is proposed with aerodynamic heat and force simulation based on computational fluid dynamics (CFD). The method utilizes laminar model based on upwind scheme and density. And the design of re-entry trajectory is made upon ISS orbit. The key technologies including re-entry characteristic analysis, flexible thermal protec-tion materials, configuration, package and Inflatable device design are shown finally.%充气式再入航天器是一种新型的再入航天器，可实现载人航天和行星探测任务中的行星大气再入，具有系统简单、质量小、气动加热低和可适应不同外形的再入载荷等优点。文章介绍了充气式再入航天器的国际发展现状，并对充气式再入航天器的总体方案进行了初步分析。参考俄罗斯的充气再入与降落技术（inflatable re-entry and descent technology，IRDT）设计先例，提出了充气式再入航天器的构型方案，并针对该构型进行了基于计算流体力学（computational fluid dynamics，CFD）的气动力和热仿真分析。计算采用了迎风格式的层流模型，基于密度进行求解。文章还基于国际空间站的运行轨道，开展了再入轨道的设计，最后对再入气动特性分析、柔性热防护材料、布局与折叠包装和充气机构设计等关键技术提出了初步建议。