The invention discloses a high-efficiency shock wave drag reduction system of a hypersonic aircraft, which realizes compression of hypersonic incoming flow by utilizing a system formed by combining aturbulent flow pipe, reverse jet flow and annular jet flow, weakens the intensity of shock waves in front of the aircraft and reduces shock wave resistance. The efficient shock wave drag reduction system of the hypersonic aircraft can greatly reduce shock wave resistance of the aircraft, improve the flight speed of the aircraft, reduce fuel carried by the aircraft and promote development of the hypersonic technology. In addition, the system has the advantages of being simple in structure and easy to manufacture, install and replace, and has universality for hypersonic aircrafts.
本发明公开了一种高超声速飞行器高效激波减阻系统,利用扰流管、反向喷流和环形喷流组合而成的系统实现对高超声速来流的压缩,减弱飞行器前方的激波强度,降低激波阻力。本发明的高超声速飞行器高效激波减阻系统能大幅降低飞行器的激波阻力,提高飞行器的飞行速度,减少飞行器所携带的燃料,推动高超声速技术的发展。此外,本发明还具有结构简单,易于制造、安装和更换的优点,且对高超声速飞行器具有通用性。
Efficient shock wave drag reduction system of hypersonic aircraft
一种高超声速飞行器高效激波减阻系统
2020-08-21
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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