Oblique detonation wave standing control method and variable geometry combustion chamber

Abstract

The invention provides an oblique detonation wave standing control method and a variable geometry combustion chamber. An engine in the method comprises an air suction type air inlet channel, the variable geometry combustion chamber, an exhaust nozzle and a control system; the combustion chamber comprises an adjustable inner wall and a fixed outer wall and is integrally designed by adopting a geometric structure; the front section of the inner wall is connected with the air inlet channel, the front section and the rear section of the inner wall are connected through a movable inflection point,and the rear section of the inner wall is connected with the exhaust nozzle; and supersonic combustible gas enters the combustion chamber after being compressed through the air inlet channel, obliquedetonation waves are generated through second oblique wedge detonation of the outer wall, monitoring signals are transmitted to an output control module to adjust the included angle between the frontsection and the rear section of the inner wall of the combustion chamber, and the position of the movable inflection point and the expansion angle of the exhaust nozzle are controlled, so that a sustainable standing oblique detonation wave is formed in the combustion chamber, and a detonation combustion product enters a supersonic spray pipe to generate thrust. According to the method, the movement interval of the detonation position can be effectively controlled, the path is automatically controlled to be optimized, the improvement and extension difficulty during engineering application is reduced, the space design is more flexible, and the practical application operability is improved.

Description

technical field [0001] The invention relates to the technical field of air-breathing hypersonic propulsion, in particular to a method for controlling oblique detonation shock wave stagnation. In addition, the present invention also relates to a variable geometry combustion chamber based on the above-mentioned oblique detonation wave stationary control method. Background technique [0002] One of the important development directions of hypersonic vehicles is higher flight Mach number and stronger maneuverability. This puts forward higher requirements on the performance of the aircraft propulsion system. However, the current traditional power technology is difficult to meet the needs of hypersonic flight. According to the theoretical analysis of thermodynamics, increasing the pressure of the exothermic zone has a significant effect on improving the performance of various engines. Detonation combustion increases the pressure of the exothermic region through shock wave compre...

AI Technical Summary

Problems solved by technology

By dynamically adjusting the position, the action position of the oblique detonation wave and the inner wall is indirectly controlled; the shortcomings of the currently disclosed implementation schemes are: the adjustment means of the dynamic control scheme is monotonous, and it completely depends on the adjustment of the detonation oblique split, and the adjustment interval of the oblique detonation limited; the thermal jet scheme sets up an additional detonation system, while weakening the influence of the inner wall, it will inevitably form a more complex wave system structure, which is not conducive to the stability of detonation combustion to a certain extent; and the above-mentioned schemes do not address the possible Short-term loss of control occurs, and corresponding solutions are given

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