The invention provides a hypersonic aircraft and a head heat and resistance reducing structure thereof. The head heat-reducing and resistance-reducing structure comprises a blunt body base which is provided with a reverse jet flow main hole and a reverse jet flow auxiliary hole. The reverse jet main hole is positioned at a stagnation point of the blunt body base; and in the incoming flow direction, the reverse jet auxiliary hole is located on the downstream side of the reverse jet main hole. According to the scheme, the required reverse jet pressure is relatively low, the original aerodynamic configuration and material strength of the blunt base are not changed, the robustness is relatively good, and the method has a relatively great engineering application prospect on a hypersonic aircraft.
本申请提供了一种高超声速飞行器及其头部降热减阻结构。头部降热减阻结构包括:钝头体基底,钝头体基底设有逆向射流主孔和逆向射流辅孔;逆向射流主孔位于钝头体基底滞止点位置处;沿来流方向,逆向射流辅孔位于逆向射流主孔的下游侧。本方案所需逆向射流压力较低,且不改变钝头基底原本的气动外形与材料强度,鲁棒性较好,在高超声速飞行器上具有较大的工程应用前景。
Hypersonic aircraft and head heat and resistance reducing structure thereof
一种高超声速飞行器及其头部降热减阻结构
2024-04-19
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Self-adaptive device for reducing resistance and heat of head of hypersonic flight vehicle
European Patent Office | 2024
|NTIS | 1964
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