The invention belongs to the technical field of pneumatic heat protection, and aims at providing an aircraft head-on resistance and heat reduction method to solve the technical problem that in the prior art, the requirement for heat protection of the aircraft is higher and higher. The configuration entity made of the material which has the heat sublimation characteristic and can be ablated in a shape-preserving mode is arranged at the front end of the aircraft in a protruding mode, on one hand, arch shock waves can be converted into conical shock waves through shape-preserving ablation of the configuration entity, so that the range of approximate normal shock waves in front of the aircraft is reduced, the wave resistance of oblique shock waves is smaller than that of the normal shock waves, and the shock wave resistance can be effectively reduced; on the other hand, heat flow borne by the surface of the aircraft body can be reduced, and heat protection is conducted on the aircraft.
本发明属于气动防热技术领域,针对现有技术中存在的对飞行器的防热的要求越来越高的技术问题,本发明的目的在于提供一种飞行器迎面减阻减热方法,通过在飞行器前端凸出设置采用具有热升华特性并能够保型烧蚀的材料制备成的构型实体,利用构型实体保型烧蚀可以一方面将弓形激波转变为锥形激波,这样飞行器前方近似正激波范围减小,由于斜激波的波阻要比正激波小,从而可以有效减小激波阻力;另一方面还可以降低飞行器主体表面承受的热流,从而对飞行器进行热防护。
Aircraft head-on resistance and heat reduction method
一种飞行器迎面减阻减热方法
2022-02-15
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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