Integrated control method and device for oblique detonation engine combustion chamber spray pipe

Abstract

The invention provides an integrated control method and device for an oblique detonation engine combustion chamber spray pipe. An engine in the method comprises an air inlet channel, an isolation section, a control system and the integrated combustion chamber spray pipe. The integrated combustion chamber spray pipe comprises a combustion chamber upper wall surface, a spray pipe inlet wall surface, a tail expansion wall surface, an air exhaust hole, a wave surface detection point and a combustion chamber lower wedge surface. Supersonic incoming flow and fuel injected by a precursor are mixed in an air inlet channel and detonated into oblique detonation waves through induction of oblique shock waves on a lower wedge surface, a signal input module is used for inputting signals, a telescopic supporting rod is adjusted, accordingly, the oblique detonation waves capable of staying continuously are formed in the combustion chamber, and detonation combustion products pass through a supersonic expansion spray pipe to generate thrust. The incoming flow angle and the inflection point position are controlled by adjusting a movable inflection point of the telescopic supporting rod, and the lower wedge surface controls the downstream wave system structure; and a suction hole is further formed, so that the reliability of the whole control system is improved, 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 an integrated control method for a combustion chamber nozzle of an oblique detonation engine. In addition, the present invention also relates to a device based on the above-mentioned integrated control method for the nozzle of the oblique detonation engine combustion chamber. Background technique [0002] With the rapid development of my country's aerospace research, supersonic ramjet propulsion is rapidly developing towards a higher Mach number. The advantages of high thermal cycle efficiency and high heat release rate of detonation combustion have laid a scientific foundation for its application in aerospace power systems, while oblique detonation ramjet propulsion can overcome the problem of stagnation without additional ignition, which is based on oblique detonation shock wave The new combustion organization method can break through the bottleneck...

AI Technical Summary

Problems solved by technology

Its shortcoming is that the key of this scheme is to adjust the wave surface position of the oblique detonation wave, but its goal is to reduce the chemical energy loss; it still does not consider whether the point of action between the wave surface and the nozzle is just at the nozzle entrance or not. Don’t pay attention to the resulting consequences; the angle of the lower wedge surface has a great influence on the overall structure of the oblique detonation. After the angle is changed, both the wave system structure of the initiation area and the stability of the oblique detonation wave surface will change; even if it can The position of the detonation wave surface can be adjusted by adjusting the angle of the wedge face to achieve the purpose of detonation wave stagnation, but it is easy to cause drastic changes in the combustion state, which is not conducive to the acquisition of stable thrust

Its shortcoming is that although the scheme considers the location of the detonation wave and assumes that it is located upstream of the nozzle, it only considers the boundary layer effect and does not pay attention to the configuration characteristic of the oblique detonation engine, w

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