A stationary control method of oblique detonation wave and variable geometry combustion chamber

Abstract

The invention provides a method for controlling oblique detonation wave stagnation and a variable geometry combustion chamber. The engine in the method includes an air-breathing inlet, a variable geometry combustion chamber, a tail nozzle, and a control system; the combustion chamber includes an adjustable inner wall and a combustion chamber. The outer wall is fixed, and the design of geometric structure is integrated; the inner wall is connected to the inlet port at the front, with a movable inflection point, and the tail nozzle is connected at the rear; supersonic combustible gas is compressed into the combustion chamber through the inlet port, and is detonated by the second oblique splitting on the outer wall to generate an oblique detonation shock wave , and transmit the monitoring signal to the output control module to adjust the angle between the front and rear sections of the combustion chamber wall, control the position of the movable inflection point and the expansion angle of the tail nozzle, so that a sustainable stationary oblique detonation shock wave is formed in the combustion chamber. The shock combustion products enter the supersonic nozzle to generate thrust. The invention can effectively control the movement interval of the detonation position, automatically control path optimization, reduce the difficulty of improvement and expansion during engineering application, make the space design more flexible, and improve the operability of practical application.

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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