IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0249059
(2008-10-10)
|
등록번호 |
US-8371104
(2013-02-12)
|
발명자
/ 주소 |
- Wells, David M.
- McCallum, Brent N.
- Ginn, Kerry B.
- Jenkins, Stewart A.
|
출원인 / 주소 |
- Lockheed Martin Corporation
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
15 |
초록
▼
A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be in
A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be integrated into a nozzle deck or side walls without the need for engine bleed to supply fluid injectors. An external fluidic vectoring system uses injectors or plasma devices located aft of the nozzle exit to vector the exhaust plume with no external moving parts. Elements of both mechanical and fluidic systems may be combined for a given application.
대표청구항
▼
1. An aircraft, comprising: a body having a propulsion system and an exhaust system located aft of the propulsion system for releasing an exhaust plume having an exhaust axis extending in a longitudinal direction; the exhaust system comprising:a nozzle having a throat, the nozzle and throat being co
1. An aircraft, comprising: a body having a propulsion system and an exhaust system located aft of the propulsion system for releasing an exhaust plume having an exhaust axis extending in a longitudinal direction; the exhaust system comprising:a nozzle having a throat, the nozzle and throat being completely enclosed by an aftbody about the exhaust axis in a radial direction to a nozzle exit station;the aftbody having a deck on a lower side and side walls on lateral sides of and extending upward from the deck about the exhaust axis, the deck and side walls extending aft from the nozzle exit station to a trailing edge of the deck, the deck being immoveable relative to the aftbody and defining a lower boundary surface for the exhaust plume, the aftbody being open above the deck from the nozzle exit station to the trailing edge of the deck; anda plurality of fluid injectors mounted to the aftbody for manipulating the exhaust plume between the throat and the trailing edge for redirecting a vector of the exhaust plume away from the exhaust axis. 2. An aircraft according to claim 1, wherein the side walls and the deck provide enclosure of the exhaust plume on three sides about the exhaust axis, with the deck extending in a substantially horizontal direction, the side walls extending from the deck in a substantially vertical direction, and the side walls having trailing edges located a same distance from the exit station as the trailing edge of the deck. 3. The aircraft according to claim 1, wherein the nozzle exit station is located between the throat and the trailing edge of the deck. 4. The aircraft according to claim 1, wherein the fluid injectors are located in the side walls for injecting a fluid at the exhaust plume for moving the exhaust plume with respect to the exhaust axis. 5. The aircraft according to claim 4, wherein the fluid injectors point inward toward the axis and toward the throat. 6. The aircraft according to claim 4, wherein the fluid injectors are located between the nozzle exit station and the trailing edge of the deck. 7. The aircraft according to claim 4, wherein the fluid injectors comprise zero-net-mass-flux effectors selected from the group consisting of synthetic jets and plasma devices. 8. The aircraft according to claim 1, wherein at least some of the fluid injectors comprise elongated slots located in the deck transverse to the exhaust axis. 9. The aircraft according to claim 1, wherein at least one of the fluid injectors is mounted in each lateral side of the deck and oriented away from the throat at an acute angle relative to a line normal to the exhaust axis. 10. The aircraft according to claim 1, further comprising a mechanical device that moves deformable sidewall portions of the side walls relative to the exhaust axis for moving the exhaust plume with respect to the exhaust axis, and the deformable side wall portions are in a location between the nozzle exit station and the trailing edge of the deck. 11. The aircraft according to claim 10, wherein the deformable side wall portions are selected from the group consisting of multiple overlapping segments or hinged segments. 12. The aircraft according to claim 10, wherein at least some of the fluid injectors are located on the deformable side wall portions. 13. The aircraft according to claim 1, wherein the fluid injectors comprise a first injector in a first direction forward of and inside the nozzle exit station, and a second injector, located outside of the nozzle exit on an external surface of the aftbody, in a second direction opposed to the first direction to entrain a freestream flow and generate shear forces by the opposed injections to form an asymmetric, high momentum streamwise vortex. 14. The aircraft according to claim 13, wherein the first and second injectors each comprise two injectors, and the first injectors are located upstream relative to the second injectors and to the nozzle exit station. 15. The aircraft according to claim 1, further comprising: a hinged segment mounted in each of the side walls aft of the nozzle exit station, each of the hinged segments being pivotal from a position flush with one of the side walls to a radially inward directed position; andone of the fluid injectors is mounted to each of the hinged segments. 16. An aircraft, comprising: a body having a propulsion system and an exhaust system located aft of the propulsion system for releasing an exhaust plume having an exhaust axis extending in a longitudinal direction; the exhaust system comprising:a nozzle having a throat and an exit station, the nozzle, the throat and the exit station being completely enclosed about the exhaust axis in a radial direction;an aftbody surrounding the exhaust system and having a deck and side walls on lateral sides of the deck about the exhaust axis, the deck and side walls extending from the nozzle exit station to a trailing edge of the deck, the aftbody being at least partially open about the exhaust axis in the radial direction, the side walls and deck providing approximately 270° of enclosure of the exhaust plume about the exhaust axis, with the deck extending in a substantially horizontal direction, the side walls extending from the deck in a substantially vertical direction, such that the deck is uncovered above the side walls and the aftbody is open aft of the nozzle exit station, and wherein the deck is in a fixed position relative to the aftbody that defines a lower side of the exhaust plume;a plurality of fluid injectors mounted to the aft body between the exit station and the trailing edge of the deck for injecting a fluid into the exhaust plume; anda mechanical device that moves deformable sidewall portions of the side walls relative to the exhaust axis for moving the exhaust plume with respect to the exhaust axis, and the deformable side wall portions are in a location between the nozzle exit station and the trailing edge of the deck. 17. The aircraft according to claim 16, wherein the nozzle exit station is located between the throat and the trailing edge of the deck. 18. The aircraft according to claim 16, wherein: the fluid injectors are located in the side walls;the fluid injectors are in a location between the nozzle exit station and the trailing edge, and one fluid injector is mounted in each side wall, and each fluid injector is oriented at an acute angle relative to the side wall. 19. The aircraft according to claim 16, wherein the fluid injectors comprise zero-net-mass-flux effectors selected from the group consisting of synthetic jets and plasma devices. 20. The aircraft according to claim 16, wherein one of the fluid injectors is mounted in each lateral side of the deck; and wherein the deck defines a deck surface having a normal direction, and the fluid injectors are oriented toward the throat at an acute angle relative to the normal direction. 21. The aircraft according to claim 16, wherein the fluid injectors apply the fluid from a first injector in a first direction forward of the nozzle exit station, and through a second injector outside and forward of the nozzle exit on the aftbody external surface in a second direction opposed to the first direction to entrain a freestream flow and generate shear forces by the opposed injections to form an asymmetric, high momentum streamwise vortex; and the first and second injectors each comprise two injectors located upstream relative to the nozzle exit station. 22. The aircraft according to claim 16, wherein the deformable side wall portions are selected from the group consisting of multiple overlapping segments or hinged segments. 23. The aircraft according to claim 16, wherein each of the deformable side wall portions comprise: a hinged segment mounted in each of the side wails, each of the hinged segments being pivotal from a position flush with one of the side walls to a radially inward directed position; andwherein one of the fluid injectors is mounted to each of the hinged segments. 24. An aircraft, comprising: a body having a propulsion system and an exhaust system located aft of the propulsion system for releasing an exhaust plume having an exhaust axis extending in a longitudinal direction; the exhaust system comprising:a nozzle having a throat and an exit station, the nozzle, the throat and the exit station being completely enclosed about the exhaust axis in a radial direction;an aftbody surrounding the exhaust system and having a deck and side walls on lateral sides of the deck about the exhaust axis, the deck and side walls extending from the nozzle exit station to a trailing edge of the deck, an upper portion of the aftbody terminating at the exit station, defining an opening above an entire extent of the deck, and wherein the deck is a fixed position relative to the aftbody that defines a lower side of the exhaust plume;a plurality of fluid injectors mounted to the side walls between the exit station and the trailing edge of the deck for injecting, a fluid into the exhaust plume;a hinged segment mounted in each of the side walls between the exit station and the trailing edge of the deck, each of the hinged segments being pivotal from a position flush with one of the side walls to a radially inward directed position; andwherein one of the fluid injectors is mounted to each of the hinged segments for movement therewith.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.