Intake and exhaust device of air breathing supersonic/hypersonic aerocraft

Abstract

The invention relates to an intake and exhaust device of an air breathing supersonic / hypersonic aerocraft, comprising an inner flow passage arranged at the lower abdomen of the aerocraft; the inner flow passage comprises an intake passage, an isolating section, a combustion chamber and a spray pipe; the intake and exhaust device also comprises an aspirator connected between the intake passage and the spray pipe and a control device for controlling the opening or closing of the aspirator; the control device controls the suction device according to the working conditions of the aerocraft; when the air breathing supersonic aerocraft works on designed points, the control device sends an instruction to close the aspirator; when the air breathing supersonic aerocraft works on non-designed points, the control device sends instruction to open the aspirator; at the moment, an incoming flow is divided into a main flow and a secondary flow, wherein the main flow passes through the inner flow passage; and the secondary flow utilizes pressure difference between a front body and a rear body to form a suction airflow by the aspirator, thus leading the intake passage and the spray pipe to be coupled to a certain degree.

Description

technical field [0001] The invention relates to an inner channel of an air-breathing supersonic / hypersonic aircraft. Background technique [0002] At present, the air-breathing hypervehicle has attracted more and more attention and attention from various countries because of its huge development potential. The interaction of the boundary layer causes the flow coefficient of the intake port to drop rapidly, resulting in large shock wave resistance and overflow resistance, deterioration of combustion efficiency and even engine failure; at the same time, the nozzle is in a state of severe over-expansion. There is a large low-pressure area on the expansion surface of the nozzle, and the thrust of the nozzle drops sharply, and at the same time, a huge nose-up moment will be generated. Therefore, the living space of the air-breathing hypersonic vehicle is severely compressed, and it is imminent to expand its flight Mach number and improve its flight performance at non-design poin...

AI Technical Summary

Problems solved by technology

[0002] At present, the air-breathing hypervehicle has attracted more and more attention and attention from various countries because of its huge development potential. The interaction of the boundary layer causes the flow coefficient of the intake port to drop rapidly, resulting in large shock wave resistance and overflow resistance, deterioration of combustion efficiency and even engine failure; at the same time, the nozzle is in a state of severe over-expansion. There is a large low-pressure area on the expansion surface of the nozzle, and the thrust of the nozzle drops sharply, and at the same time, a huge torque will be generated

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