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.
Supersonic-velocity hypersonic-velocity gas inlet duct adopting pneumatic unstart control method
2015-09-09
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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