可重复使用飞行器热走廊物理建模研究

对再入热走廊的物理含义进行了定义分析,为使防热层温度不超过热防护系统所允许使用的极限温度,可重复使用飞行器的飞行轨道必须在再入走廊热之内。建立了可重复使用飞行器再入热走廊的物理模型,给出该物理模型下热走廊的控制方程和求解方法。通过对航天飞机轨道器典型位置的再入热走廊与传统方法的验证分析,说明本文建立的可重复使用飞行器再入热走廊物理模型和求解方法是正确的,同时探讨了表面材料承受温度和发射系数对热走廊的影响规律。

PHYSICAL MODEL ESTABLISHMENT FOR THE THERMAL CORRIDOR OF A REUSABLE LAUNCH VEHICLE

The concept of thermal corridor for a reusable launch vehicle is specified and analyzed. The reentry trajectory for a RLV should be restricted within its corresponding thermal corridor in order that the TPS temperature is not exceed its temperature limitation. The upper and lower margins of the thermal corridor are determined by physical-chemical character of the TPS material. The physical model for the thermal corridor of a RLV is established, and the governing equations and solution method for the thermal corridor are studied. The temperature analyses along the reentry trajectory for the typical locations on Space Shuttle Orbiter are investigated by both thermal corridor and traditional method, and the results indicated that the thermal corridor model and the solution method are feasible and effective. Finally, the effects of the temperature limit and the emissivity of surface material on the thermal corridor are analyzed.