Passive jet spoiler for yaw control of an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-021/02
B64C-021/00
출원번호
US-0229971
(2002-08-28)
발명자
/ 주소
McClure,Paul D.
출원인 / 주소
Lockheed Martin Corporation
대리인 / 주소
Bracewell &
인용정보
피인용 횟수 :
20인용 특허 :
6
초록▼
A wing for an aircraft has a passive jet spoiler for providing yaw control by increasing drag on the wing. The spoiler comprises an inlet located near the leading edge of a lower surface of the wing and at least one outlet formed on the lower surface or on an upper surface of the wing. An internal p
A wing for an aircraft has a passive jet spoiler for providing yaw control by increasing drag on the wing. The spoiler comprises an inlet located near the leading edge of a lower surface of the wing and at least one outlet formed on the lower surface or on an upper surface of the wing. An internal passage connects the inlet and each outlet for allowing air to pass from the inlet to the outlet. The air exits the outlets generally normal to the respective surface of the wing, causing a laminar flow to separate from the surfaces downstream of each outlet. The separated flow increases the drag on the wing, producing a yawing moment on the aircraft. Selective placement of the outlets on the upper and lower surfaces limits undesirable roll and pitch moments. Valves are provided for selectively controlling the amount of air passing through the spoiler.
대표청구항▼
I claim: 1. An airfoil having an outer surface with an upper side, an opposing lower side, a leading edge, and a trailing edge, the airfoil comprising: an inlet located on the outer surface of the airfoil; an upper outlet located on the upper side of the airfoil and a lower outlet located on the lo
I claim: 1. An airfoil having an outer surface with an upper side, an opposing lower side, a leading edge, and a trailing edge, the airfoil comprising: an inlet located on the outer surface of the airfoil; an upper outlet located on the upper side of the airfoil and a lower outlet located on the lower side of the airfoil, each outlet positioned in fluid communication with the inlet and positioned forward of the trailing edge of the airfoil; wherein the upper and lower outlets are positioned so that when a portion of air flowing adjacent the outer surface is diverted into the inlet and out the outlets, the portion of air causes an attached air flow to become separated from the outer surface downstream of each of the outlets through which the portion of air flows, substantially forward of the trailing edge of the airfoil; and at least one valve between the inlet and the outlets for controlling air flow from the inlet to the outlets. 2. The airfoil of claim 1, wherein: the inlet is located forward of a midpoint along a chord of the airfoil and the outlets are located aft of the midpoint of the chord of the airfoil. 3. The airfoil of claim 1, wherein: the inlet is located on the lower side of the airfoil. 4. The airfoil of claim 1, wherein: said at least one valve has a first position wherein the air flow through the inlet passes only through one of the outlets and a second position wherein the air flow through the inlet passes through only the other of the outlets. 5. The airfoil of claim 4, wherein: said at least one valve has a third position that causes more air flow through one of the outlets than the other of the outlets. 6. The airfoil of claim 1, wherein: the at least one valve is a sliding gate type valve selectively movable between an open position, which allows air to freely flow past the valve, a closed position, which blocks the flow of air past the valve, and a partially open position, which allows a reduced amount of flow of air past the valve. 7. The airfoil of claim 1, wherein: the at least one valve comprises a plate that slidingly engages an adjacent cover, each of the plate and the cover having openings therethrough, the openings of the plate and the cover being aligned when the at least one valve is in the open position, the openings being misaligned when the at least one valve is in the closed position. 8. An airfoil having an outer surface with an upper side and a lower side, comprising: an inlet located on the outer surface of the airfoil; an upper outlet located on the upper side of the airfoil and a lower outlet located on the lower side of the airfoil, one of the outlets spaced longitudinally downstream of the other of the outlets and each outlet being in fluid communication with the inlet and positioned so that a portion of air flowing adjacent the outer surface is diverted into the inlet and out the outlets to thereby cause an attached air flow to become separated downstream of each of the outlets through which the portion of air flows; and at least one valve between the inlet and the outlets for controlling air flow from the inlet to the outlets. 9. An airfoil having an outer surface with an upper side and a lower side, comprising: an inlet located on the outer surface of the airfoil; an upper outlet located on the upper side of the airfoil and a lower outlet located on the lower side of the airfoil, a main passage leading from the inlet toward the outlets and each outlet being in fluid communication with the inlet and positioned so that a portion of air flowing adjacent the outer surface is diverted into the inlet and out the outlets to thereby cause an attached air flow to become separated downstream of each of the outlets through which the portion of air flows; upper and lower passages joining the main passage at a Y-junction and leading to the upper and lower outlets; and a valve between the inlet and the outlets for controlling air flow from the inlet to the outlets, the valve located at the Y-junction and selectively movable between a first position, in which substantially all of the portion of air is directed into one of the outlets, and a second position, in which substantially all of the portion of air is directed into the other of the outlets. 10. An aircraft having a yaw control system, the aircraft having upper and lower surfaces forming a wing profile having a leading edge and enclosing an interior volume, the system comprising: an inlet located on the lower surface aft of the leading edge, forward of a midpoint of a chord of the wing, and being in fluid communication with an internal passage located within the interior volume; an upper outlet located on the upper surface and longitudinally spaced downstream of the inlet aft of the midpoint of the chord, the upper outlet being in fluid communication with the internal passage; a lower outlet located on the lower surface and longitudinally spaced downstream of the inlet aft of the midpoint of the chord, the lower outlet being in fluid communication with the internal passage; and wherein the upper and the lower outlets are positioned so that a portion of air flowing adjacent the lower surface is diverted into the inlet, through the internal passage, and selectively out of both the upper and lower outlets to cause an attached air flow to become separated from the upper surface downstream of the upper outlet and from the lower surface downstream of the lower outlet to thereby control aircraft yaw. 11. The system of claim 10, further comprising: at least one valve for controlling the amount of air passing through the internal passage, the valve being located in one of the inlet, internal passage, and upper and lower outlets. 12. The system of claim 11, wherein: the at least one valve is a rotatable butterfly type valve selectively movable between an open position, which allows air to freely flow past the valve, and a closed position, which restricts the flow of air past the valve. 13. The system of claim 11, wherein: the at least one valve is a sliding gate type valve selectively movable between an open position, which allows air to freely flow past the valve, and a closed position, which restricts the flow of air past the valve. 14. The system of claim 13, wherein: the sliding gate type valve comprises a plate that slidingly engages an adjacent cover, each of the plate and the cover having openings therethrough, the openings of the plate and the cover being aligned when the valve is in the open position, the openings being misaligned when the valve is in the closed position. 15. The system of claim 10, further comprising: a valve selectively movable between a first position, in which substantially all of the portion of air is directed into the upper outlet, and a second position, in which substantially all of the portion of air is directed into the lower outlet, the valve also being selectively positionable between the first and second positions for diverting a selected amount of the portion of air into each of the outlets. 16. A method for controlling yaw of an aircraft having an airfoil with an outer surface having upper and lower sides, the method comprising: (a) forming an air inlet on the outer surface, first and second outlets on opposite and opposing sides of the outer surface, the outlets being spaced downstream from the inlet, the inlet and the outlets being connected to each other within the airfoil; (b) propelling the aircraft through air for causing air to flow across the outer surfaces of the airfoil; and (c) diverting a first portion of the air flowing across the outer surface into the inlet and out the first outlet, the first portion of air causing an attached airflow to become detached from the outer surface downstream of the first outlet thereby increasing drag for controlling yaw; and (d) diverting a second portion of the air flowing across the outer surface into the inlet and out the second outlet when diverting the first portion of the air to reduce any pitch and roll moments caused by the first portion of air flowing out the first outlet. 17. The method of claim 16, wherein: step (a) further comprises forming the inlet on a lower surface of the airfoil forward of a midpoint of the chord of the airfoil.
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