Supersonic-velocity hypersonic-velocity gas inlet duct adopting pneumatic unstart control method

Abstract

The invention provides a supersonic-velocity hypersonic-velocity gas inlet duct adopting a pneumatic unstart control method. The gas inlet duct comprises an gas inlet duct front body, an gas inlet duct lip hood, an inner-channel lower wall plate and a pneumatic control system, wherein the pneumatic control system is arranged in the gas inlet duct front body, and comprises a multi-seam plate, wherein the multi-seam plate covers a first pressure stabilizing cavity; a second pressure stabilizing cavity is also formed on the inner-channel lower wall plate, a cap body and an injection channel communicated with the inner part of the second pressure stabilizing cavity and the inlet of the gas inlet duct are arranged on the second pressure stabilizing cavity; the first pressure stabilizing cavity and the second pressure stabilizing cavity are connected with a high-pressure gas source through respective gas introduction pipes and valves, the valves comprise pressure regulating valves and electromagnetic valves, the pressure regulating valves are used for regulating the flow and the pressure of the injected gas, and the electromagnetic valves are used for quickly powering on and off. The high-pressure gas is controlled by the valves to be injected in the gas inlet duct from the horizontal injection channel or from rows of oblique seams, so that the supersonic-velocity hypersonic-velocity gas inlet duct disclosed by the invention can quickly perform subcritical oscillation suppression and restart control on the gas inlet duct.

Description

technical field [0001] The invention relates to the field of supersonic and hypersonic air intakes for aircraft, in particular to fixed geometry air intakes. Background technique [0002] As a key aerodynamic component of an air-breathing high-speed propulsion system and an important factor in airframe / propulsion system integration, the design form and working characteristics of supersonic and hypersonic inlets directly affect the overall performance of the propulsion system. Correlation analysis results show that for a hydrogen-fueled scramjet engine working on Mach 5, every 1% increase in the compression efficiency of the intake port can lead to a 0.5%-1% increase in the specific impulse of the engine, and every 1% increase in the flow capture efficiency Boosting results in a 0.4% increase in the specific impulse of the engine. For this reason, the design form and aerodynamic performance of the inlet are quite critical. There has been a lot of research work devoted to the...

AI Technical Summary

Problems solved by technology

From the perspective of aerodynamic principle, the above methods of inlet overflow and air release in the channel can respectively control the non-starting state of supersonic and hypersonic inlets. However, due to the relatively large movable parts and strokes involved, the above control measures The rapid response ability is doubtful, and the real-time performance is difficult to be guaranteed

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