[특허]Relating to air-breathing flight vehicles

MBDA UK Limited

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Relating to air-breathing flight vehicles

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-033/02
미국특허분류(USC)	244/207; 244/035A; 244/053B
출원번호	US-0640579 (2009-12-17)
등록번호	US-8662453 (2014-03-04)
우선권정보	EP-08253441 (2008-10-23); GB-0819473.0 (2008-10-23)
발명자 / 주소	Richards, Clifford John
출원인 / 주소	MBDA UK Limited
대리인 / 주소	Buchanan Ingersoll & Rooney PC
인용정보	피인용 횟수 : 2 인용 특허 : 12

초록
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An air intake for a supersonic air-breathing flight vehicle introduces or injects fluid in order to create predetermined regions of separated flow and an attendant fluid shear layer. This shear layer forms an aerodynamic boundary for the capture flow with a profile determined and optimised by appropriate injection of fluid. The aerodynamic boundary so generated replaces mechanically moveable solid surfaces used to vary the geometry of prior-art intakes. Use of an introduced or injected fluid can provide an advantage of a variable geometry, but with reduced weight and reduced mechanical complexity. In some embodiments, the injection of fluid has the effect of re-energizing any ingested boundary layer, thus obviating the conventional requirement for a bleed system to provide boundary layer control.

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1. A method of controlling a location of shock waves generated at a leading edge of an engine intake of an engine in a powerplant of a supersonic vehicle, the engine intake comprising a surface providing the leading edge and a cowl having a cowl lip downstream of the leading edge, so that the shock wave extends in an optimum orientation relative to the cowl lip, the method comprising: downstream of the leading edge and upstream of the cowl lip, injecting air into an air flow captured by the air-intake, the air being injected through or adjacent the surface providing the leading edge in a direction neither parallel nor substantially parallel to the air flow, and under sufficient pressure for the injected air to penetrate into the captured airflow,whereby a region of separated flow and a shear layer are formed in the captured airflow for controlling effective shape of the compression surfaces of a supersonic engine intake, andwherein at least one of the direction and the pressure of injection is controlled depending on the velocity of the vehicle so that the shock wave extends in an optimum orientation relative to the cowl lip for optimising the associated shock system geometry. 2. The method of claim 1, wherein the direction and pressure of injection is controlled depending on the velocity of the vehicle so that the shock wave extends onto the cowl lip. 3. The method of claim 1, further comprising injecting air into the air flow at a high angle relative to the air flow direction, in order to prevent buzz or react to engine failure. 4. The method of claim 1, further comprise using the injected air to re-energise the boundary layer of the air flow. 5. A supersonic-flight vehicle structure for a vehicle, the structure comprising: an engine having an engine intake comprising a surface providing a leading edge which generates shock waves during supersonic flight, and a cowl having a cowl lip downstream of the leading edge;an outlet through or adjacent the surface providing the leading edge, the outlet being located downstream of the leading edge and upstream of the cowl lip, in the engine intake, and being connected to a source of pressurised air so that air is ejected out of the outlet in a direction neither parallel nor substantially parallel to the air flow captured by the intake, and under sufficient pressure for the ejected air to penetrate into the air flow captured by the intake, whereby a region of separated flow and a shear layer are formed in the air flow captured by the intake for controlling effective shape of the compression surfaces of the engine intake thereby controlling an orientation of shock waves generated at the leading edge; anda control being configured to control at least one of the direction and pressure of the air that is ejected out of the outlet depending on the velocity of the vehicle so that the shock waves extend in an optimum orientation relative to the cowl lip for optimising the associated shock system geometry at the engine intake. 6. A vehicle structure as claimed in claim 5, in which the outlet comprises a plurality of apertures, which are arranged to provide a plurality of independent jets of ejected air, or one or more combined jet. 7. A vehicle structure as claimed in claim 5, in which the air intake is substantially rectangular and the outlet is elongate or comprises a plurality of apertures forming a line, such that the ejected air initially forms a substantially flat surface. 8. A vehicle structure as claimed in claim 5, in which the air intake is axi-symmetric, and the outlet is a ring, or comprises a plurality of apertures forming a ring, such that the ejected air initially forms an axi-symmetric surface. 9. A vehicle structure as claimed in claim 5, wherein the control is configured to control the direction and pressure of the ejected air depending on the velocity of the vehicle so that the shock waves extend onto the cowl lip. 10. A vehicle structure as claimed in claim 5, in which the outlet comprises a cylinder that is rotatable relative to a surface of the vehicle structure, the rotatable cylinder comprising an aperture, from which the air that is ejected out of the outlet is ejected, connected to the source of pressurised air. 11. A vehicle structure as claimed in claim 5, in which the outlet comprises a flap that is rotatably pivoted relative to a surface of the vehicle structure, the flap being adjacent to an aperture, from which the air that is ejected out of the outlet is ejected, connected to the source of pressurised air. 12. A vehicle structure as claimed in claim 5, in which the source of air is a reservoir of air at a pressure higher than the pressure of air flowing past the outlet. 13. A vehicle structure as claimed in claim 5, in which the source of air is a high-pressure bleed from a compressor in a powerplant of the vehicle. 14. A vehicle structure as claimed in claim 5, in which the source of air is a bleed from an intake diffuser of the air intake.

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 2

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Relating to air-breathing flight vehicles

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Relating to air-breathing flight vehicles

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이 특허에 인용된 특허 (12)

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