Dynamic boundary control system for detonation dynamic stable propagation in supersonic airflow

Abstract

The invention provides a dynamic boundary control system for detonation dynamic stable propagation in a supersonic airflow. The dynamic boundary control system comprises a detonation wave state monitoring system, an information analysis module and an expansion wall face adjustment and control system. When a detonation wave face position is monitored by the detonation wave state monitoring system to reach a set wave face critical position, an expansion wall power system is enabled; when the propagation state of the detonation wave is attenuation back-pass and the detonation wave reaches a detonation wave back-pass threshold position, an expansion angle of the expansion wall face is decreased, and the detonation wave is made to pass forwards till to reach a relatively stable dynamic standingposition; when the propagation state of the detonation wave is overdrive forward-pass and the detonation wave reaches a detonation wave forward-pass threshold position, the expansion angle of the expansion wall face is increased, the detonation wave is made to pass backwards till to reach the relatively stable dynamic standing position; and when the detonation wave is monitored to reach the dynamic standing position, the expansion wall face adjustment and control system is turned off, so that the relative dynamic stable propagation of the detonation wave is realized, and the continuous thrustis generated.

Description

technical field [0001] The invention relates to the technical field of vibration stable propagation control, in particular to a control system for realizing dynamic and stable propagation of detonation in a supersonic expansion profile combustion chamber. 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...

AI Technical Summary

Problems solved by technology

The scramjet engine has gradually moved towards engineering applications, but the conceptual design of a new scramjet engine based on detonation combustion has not yet been reported

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