X43高超声速飞行器的飞行热走廊研究

建立飞行器的热走廊物理模型和求解方法对于设计飞行器防热结构、确定飞行轨道和优化气动外形等均有重要的工程应用价值,本文对X43高超声速飞行器的飞行热走廊的物理含义进行了分析,初步建立了飞行热走廊的物理模型,给出了该物理模型下飞行热走廊的控制方程和求解方法,通过对X43高超声速飞行器典型位置的飞行热走廊的计算,研究了高超声速飞行器的热走廊规律和特征,研究了防热材料的性能对飞行走廊的限制,明确了防热材料的关键防热参数,通过研究发现: (1)防热材料的发射系数越大,其对应的热走廊越宽阔,飞行轨道的选择余地也越大; (2)不同位置、不同流态对应的热走廊边界不同,推迟转捩发生可以增加热走廊区域,有利于防热.

THE RESEARCH OF THE THERMAL CORRIDOR OF THE X43

The establishment of the physical model and solution method for the thermal corridor have greatly engineering value for the design of the thermal protection structure,choosing trajectory and the optimization design of aerodynamic outline etc.In this paper,the concept of thermal corridor for the X43 is analyzed.The physical model is established and the governing equations and solution method for the thermal corridor are studied.The thermal corridor of the typical position of the X43 is calculated and the regulation and characteristics of the thermal corridor are summarized,the limit of the thermal protection material to thermal corridor is discussed and the key parameter of the thermal protection material is defined..The results indicate:1,The larger is the emission coefficient of the surface material,the broader is the corresponding thermal corridor,and the wider is the trajectory. 2,The thermal corridor boundary changes with the position and flow.Remitting the transition can broaden the thermal corridor and favors to the thermal protection.