Knock stabilization control system and control method for scramjet engine

Abstract

The invention discloses a scramjet knock stabilization control system and method. A scramjet, a knock wave state monitoring system and a wall face boundary suction control system are included. A hot jet flow device on a scramjet conducts hot jet flow jetting on a combustion chamber of the scramjet, knock detonation is achieved, meanwhile, the knock wave state monitoring system detects the real-time spreading position of knock waves in the combustion chamber of the scramjet in real time, the wall face boundary suction control system determines the current effective suction area according to thereal-time spreading position information of the knock waves, a suction device is started to conduct wall face boundary suction on the effective suction area, and along with forward spreading of the knock waves, the real-time spreading positions of the knock waves are dynamically changed. The wall face boundary suction system dynamically changes the effective suction area corresponding to the suction device according to the changes of the real-time spreading positions of the knock waves, and accordingly, reliable detonation of the knocks in the combustion chamber of a supersonic velocity knockengine and stable self-restraint spreading control over the knocks in the supersonic velocity flow field are achieved.

Description

technical field [0001] The invention relates to the technical field of knock dynamic stable propagation control under the condition of supersonic incoming flow, in particular to a scramjet knock stable control system and a control method thereof. Background technique [0002] The scramjet engine (Scramjet) has excellent performance under high Mach (Ma>5) flight conditions, and has become the preferred solution for the propulsion system of hypersonic aircraft. However, combined with the current research and the US X-51A flight test, it can be known that the acceleration performance of the scramjet demonstrator is not obvious, and the net thrust is relatively small. Therefore, based on current research, there is an urgent need to improve engine thrust performance. The scramjet engine is designed according to the Brayton isobaric combustion cycle, and its thermodynamic cycle efficiency is much lower than that of the detonation combustion of the approximate constant volume c...

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Problems solved by technology

[0004] At present, researches on detonation in supersonic flow are still rare in the world. On the one hand, the research on detonation is mainly concentrated in still gas. is quite large, while the self-sustained propagation control of detonation under supersonic oncoming flow conditions is less studied

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