充气式返回舱气动热特性研究

摘要

According to the requirement of real-time reentry for a spacecraft, this paper presents a detailed analysis of aerodynamics for Inflatable Reentry Decelerator’s reentry from the International Space Station, during which aerodynamic heating is especially considered. Based on the heat transfer calculation methods, theory of molecular motion, Kemp-Riddell and Linear bridge functions, the heat transfer simulation models are established in free-stream regime, transitional flow regime, and continuum regime of hypersonic condition, and the heat flux of stagnation can be calculated, as well as stagnation temperature. The effects of the structural pa-rameters such as maximum diameter ofD1and half cone angleαon the characteristics of aerodynamic heating are analyzed and it is demonstrated that stagnation heat flux and temperature can be reduced apparently asD1 andαincrease to some extent. For the area near the peak stagnation heating, the heights 70km and 80km are chosen to be specially studied on their characteristics of aerodynamic heating as the Mach number increases. The thermal protection system (TPS) materials are chosen and arranged. According to the layout, temperatures at various layers are calculated with the surface heat flux distribution as outer boundary condition.%文章针对航天器返回实时性和经济性的需求，以充气式返回舱为研究对象，研究该飞行器从空间站返回过程中的气动特性，重点分析气动热特性。文章通过引入分子运动论、Kemp-Riddell方法、Linear 桥函数等计算方法，建立起该飞行器在自由分子流区、过渡流区和连续流区高超声速情况下的表面热平衡方程，得出了该飞行器返回过程中的驻点热流密度和驻点壁面温度。计算分析了该飞行器最大直径D1和半锥角α等几何尺寸对其气动热特性的影响，得到在一定范围内增大D1和α可以有效减小驻点热流密度和驻点壁面温度，并研究在峰值加热高度附近70km、80km处不同马赫数下的气动热特性。在此基础上，依据热防护系统材料和布局，将气动加热计算的表面热流分布作为外壁边界条件，分析了结构材料层的温度变化特性。