[특허]Thrust vectoring system and method

The Boeing Company

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특허 상세정보

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Thrust vectoring system and method

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-001/00 B63H-025/46 B63H-011/10
미국특허분류(USC)	060/231; 060/770; 239/265.17; 239/265.19; 239/265.23
출원번호	US-0828380 (2007-07-26)
등록번호	US-8240125 (2012-08-14)
발명자 / 주소	Kawai, Ronald Tatsuji
출원인 / 주소	The Boeing Company
대리인 / 주소	Harness, Dickey & Pierce, P.L.C.
인용정보	피인용 횟수 : 1 인용 특허 : 29

초록
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A method and system for thrust vectoring a primary fluid flow from an exhaust nozzle of a jet engine that significantly increases the non-axial force able to be generated by a flight control surface associated with the nozzle. In one implementation the method involves placing a flight control element having a movable portion adjacent a downstream edge of the nozzle. A secondary fluid flow is created adjacent a surface of the flight control element that influences a boundary layer of the primary fluid flow over the flight control element. This causes the primary fluid flow to generate a force that is directed non-parallel (i.e., non-axial) to a longitudinal axis of the nozzle. In one specific implementation a plurality of slots are formed in the flight control surface, and the flight control surface is formed by an airfoil. In another implementation the flight control surface is formed on an interior wall of the nozzle at a downstream edge of the nozzle. In various implementations either a pressurized secondary fluid flow can be directed out through the slot, or a vacuum force can be generated through the slot to either promote attachment or separation of the primary fluid flow passing over the flight control surface.

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1. A method for thrust vectoring a primary fluid flow from a jet engine, the method comprising: providing a nozzle through which the primary fluid flow flows when existing the jet engine;forming a flight control surface adjacent a downstream edge of said nozzle, the flight control surface being formed to include an airfoil that projects out beyond a downstream edge of the nozzle;providing the airfoil with a fixed component and a flap disposed at a downstream end of the fixed component, and coupled pivotally to the fixed component for movement relative to the fixed component, the fixed component being at least partially disposed within the nozzle; andgenerating a secondary fluid flow through an interior area of a portion of said airfoil such that said secondary fluid flow flows through at least one opening in said fixed component of the airfoil in a manner to generate a force on a boundary layer of said primary fluid flow flowing over said airfoil and said flap, to controllably enhance and inhibit separation of said primary fluid flow relative to said flap to control thrust vectoring of said primary fluid. 2. The method of claim 1, wherein said generating a secondary fluid flow through at least one opening comprises forming a flight control surface with a plurality of openings through which the secondary fluid flow is able to flow. 3. The method of claim 1, further comprising using an actuator to move said flap of said airfoil, and further disposing said flap such that said flap is located downstream of said downstream edge of said nozzle. 4. The method of claim 1, wherein creating a secondary fluid flow adjacent a surface of said flight control surface comprises generating a pressurized fluid flow tangential to said flight control surface to promote attachment of said primary fluid flow to said flight control surface. 5. The method of claim 1, wherein creating a secondary fluid flow adjacent a surface of said flight control surface comprises generating a pressurized fluid flow directed generally normal to said fixed component of said airfoil, to promote separation of said primary fluid flow from said flap of said airfoil. 6. The method of claim 1, wherein creating a secondary fluid flow adjacent a surface of said flight control surface comprises generating a suction airflow adjacent said flight control surface, to promote separation of said primary flow from said flight control surface. 7. The method of claim 1, wherein creating a secondary fluid flow comprises using at least one slot formed in said fixed component of said airfoil to pass said secondary fluid flow therethrough. 8. The method of claim 1, wherein the operation of forming a flight control surface comprises forming a plurality of openings to form a porous area through which said secondary fluid flow is developed. 9. A method for thrust vectoring a primary fluid flow exiting a nozzle of a jet engine, comprising: placing an airfoil having a movable flap adjacent a downstream edge of said nozzle such that a fixed component of said airfoil is located partially within said nozzle; andcontrolling movement of the flap with an actuating component, said flap being disposed outwardly of the nozzle and downstream of a downstream edge of said fixed component; andcontrollably creating a secondary fluid flow adjacent from within an interior area of said fixed component that communicates with an outer surface of said fixed component of said airfoil, such that said secondary fluid flow flows in either one of two directions generally normal to a boundary layer of said primary fluid flow over said outer surface of said flap of said airfoil, to generate forces that are directed non-parallel to a longitudinal axis of said nozzle, that augments both separation and attachment of the boundary layer relative to said flap, to control thrust vectoring of said primary fluid flow. 10. The method of claim 9, wherein creating a secondary fluid flow adjacent a surface of said airfoil comprises generating a pressurized fluid flow through an opening in said outer surface of said airfoil, wherein the pressurized fluid flow is directed tangential to said outer surface of said airfoil to promote attachment of said primary fluid flow to said airfoil. 11. The method of claim 9, wherein creating a secondary fluid flow adjacent said outer surface of said airfoil comprises generating a pressurized fluid flow through an opening in said outer surface that is directed generally normal to said outer surface of said fixed component of said airfoil, to promote separation of said primary fluid flow from said airfoil. 12. The method of claim 9, wherein creating a secondary fluid flow adjacent said outer surface of said airfoil comprises generating a suction force through an opening formed in said outer surface to promote separation of said primary fluid flow from said airfoil. 13. The method of claim 9, wherein creating a secondary fluid flow comprises using at least one slot formed in said fixed component of said airfoil to pass a secondary fluid flow therethrough. 14. A method for thrust vectoring a primary fluid flow from a jet engine, the method comprising: providing a nozzle through which the primary fluid flow flows when existing the jet engine;forming a flight control surface adjacent a downstream edge of said nozzle, the flight control surface being formed to include an airfoil that projects out beyond a downstream edge of the nozzle;providing the airfoil with a fixed component and a flap disposed at a downstream end of the fixed component, and coupled pivotally to the fixed component for movement relative to the fixed component, the fixed component being at least partially disposed within the nozzle; andgenerating a secondary fluid flow through an interior area of a portion of said airfoil such that said secondary fluid flow flows through openings in said fixed component of the airfoil in a direction that generates a force on a boundary layer of said primary fluid flow flowing over said airfoil and said flap, to control separation of said boundary layer from said flap, to control thrust vectoring of said primary fluid flow.

이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 1

Evulet, Andrei. Fluidic propulsive system and thrust and lift generator for aerial vehicles. USP20190210207812.

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Thrust vectoring system and method

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