The invention discloses a supersonic-speed or hypersonic-speed aircraft heat reduction structure and a heat reduction method, which are characterized in that by arranging the supersonic-speed or hypersonic-speed aircraft heat reduction structure, the angle of a first shock wave at an upstream shock wave is increased; therefore, the shock wave-shock wave interference mode at the upstream shock wave position and the downstream shock wave position of the aircraft is converted into V-type shock wave-shock wave interference or VI-type shock wave-shock wave interference from IV-type shock wave-shock wave interference or IVr-type shock wave-shock wave interference. The method is applied to the field of thermal protection, effective heat reduction is achieved by suppressing shock wave-shock wave interference, compared with a method for directly eliminating interference, the method is more feasible and has the practical application potential, the complexity of interference can be effectively overcome, the heat reduction effect is improved, the complexity and cost of technology implementation are reduced, and the method is suitable for popularization and application. The thermal management effect of supersonic or hypersonic aircrafts is improved, the performance and safety of the aircrafts are positively influenced, and a brand new method is provided for thermal protection of the aircrafts.
本发明公开了一种超声速或高超声速飞行器降热结构及降热方法,通过设置超声速或高超声速飞行器降热结构,增大上游激波处第一激波的角度,从而将飞行器上游激波处与下游激波处的激波‑激波干扰模式由第Ⅳ类激波‑激波干扰或第Ⅳr类激波‑激波干扰转变为第Ⅴ类激波‑激波干扰或第Ⅵ类激波‑激波干扰。本发明应用于热防护领域,通过抑制激波‑激波干扰从而实现有效的降热,相对于直接消除干扰的方法更加可行且具有实际应用的潜力,能够有效地克服干扰的复杂性,提高降热效果,并降低了技术实施的复杂性和成本,提高超声速或高超声速飞行器的热管理效果,并对飞行器性能和安全性产生积极影响,为飞行器热防护提供了全新方法。
Supersonic-speed or hypersonic-speed aircraft cooling structure and cooling method
一种超声速或高超声速飞行器降热结构及降热方法
2024-01-02
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
COOLING FOR HYPERSONIC AIRCRAFT STRUCTURES
SAE Technical Papers | 1961
|Internal convective cooling systems for hypersonic aircraft
TIBKAT | 1975
|