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液体冲压发动机的飞行速度超过马赫数(Ma)3时,气动加热情况急剧增加,高速带来的高温问题就会给冲压发动机的结构设计和设备布局带来困难。高速飞行的冲压发动机热环境主要由动力系统和气动加热两部分组成。按照传统的传热计算方法,可确定燃烧室部位的热环境数据,气动加热则与工作条件、飞行状态密切相关,在工程应用方面还需要考虑环境温度、太阳辐射、飞行器的颜色、冲击波等条件。
Liquid ramjet flight speed exceeds Mach 3 (Ma) 3, the dramatic increase in aerodynamic heating, high temperature problems caused by the stamping engine structure design and equipment will cause difficulties. High-speed flight of the ramjet engine thermal environment mainly by the dynamic system and aerodynamic heating of two parts. According to the traditional method of heat transfer calculation, the thermal environment data of the combustion chamber can be determined. The pneumatic heating is closely related to the working conditions and the flight status. In the engineering application, environmental temperature, solar radiation, aircraft color, shock wave and other conditions .