Translational thrust system for a rotary wing aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B63H-003/04
B64D-035/06
출원번호
UP-0623105
(2007-01-15)
등록번호
US-7758310
(2010-08-09)
발명자
/ 주소
Cotton, Bryan S.
Arifian, Kenneth C.
Schweizer, Leslie
Cevette, Jeffrey L.
출원인 / 주소
Sikorsky Aircraft Corporation
대리인 / 주소
Carlson, Gaskey & Olds PC
인용정보
피인용 횟수 :
7인용 특허 :
10
초록▼
A translational thrust system for a high speed rotary-wing aircraft includes a propeller system driven by a propeller gearbox, a hydraulic system, and a mechanical-hydraulic control system. The mechanical-hydraulic control system utilizes a hydraulic fluid which travels to and from a propeller dome
A translational thrust system for a high speed rotary-wing aircraft includes a propeller system driven by a propeller gearbox, a hydraulic system, and a mechanical-hydraulic control system. The mechanical-hydraulic control system utilizes a hydraulic fluid which travels to and from a propeller dome via an oil transfer/position feedback tube which translates with a propeller pitch change piston. Translation of the oil transfer/position feedback tube and the propeller pitch change piston pitches the blades between high (coarse) and low (fine) pitch positions.
대표청구항▼
What is claimed is: 1. A translational thrust system for a rotary-wing aircraft comprising: a propeller system which includes a propeller hub and a plurality of propeller blades which rotate about a propeller rotational axis transverse to a main rotor system axis of rotation; a propeller pitch chan
What is claimed is: 1. A translational thrust system for a rotary-wing aircraft comprising: a propeller system which includes a propeller hub and a plurality of propeller blades which rotate about a propeller rotational axis transverse to a main rotor system axis of rotation; a propeller pitch change piston within said propeller hub, said propeller pitch change piston mechanically linked to said plurality of propeller blades; and a mechanical-hydraulic control system in communication with said propeller system, said mechanical-hydraulic control system includes an oil transfer/position feedback tube mounted to said propeller pitch change piston, said propeller pitch change piston and said oil transfer/position feedback tube mounted for translational movement along said propeller rotational axis relative to said propeller hub to change a pitch of said plurality of propeller blades, said propeller pitch change piston mounted to said oil transfer/position feedback tube for rotation relative thereto. 2. The system as recited in claim 1, further comprising a Fly-By-Wire (FBW) flight control system to directly control a valve system to translate said oil transfer/position feedback tube in response to a position sensor system in communication with said oil transfer/position feedback tube. 3. The system as recited in claim 1, wherein said propeller pitch change piston is mounted for translational movement within said propeller hub. 4. The system as recited in claim 1, wherein said propeller pitch change piston is mounted to said oil transfer/position feedback tube for rotation therewith. 5. The system as recited in claim 1, wherein said propeller rotational axis is transverse to a main rotor system axis of rotation, said main rotor system includes a coaxial contra-rotating rotor system. 6. The system as recited in claim 1, wherein said mechanical-hydraulic control system includes a pitch stop which fail-safes said propeller system to a flat pitch. 7. The system as recited in claim 6, wherein said pitch stop is selectively overridden in response to a pilot control. 8. The system as recited in claim 1, wherein said mechanical-hydraulic control system includes a propeller dump valve which dumps a hydraulic pressure to fail-safe said propeller system to a flat pitch. 9. The system as recited in claim 8, wherein said propeller dump valve communicates, with said propeller hub to dump a hydraulic fluid therefrom. 10. The system as recited in claim 1, wherein said mechanical-hydraulic control system communicates with said propeller system to provide proportional control of said pitch of said plurality of propeller blades. 11. The system as recited in claim 1, wherein said mechanical-hydraulic control system includes a shuttle valve system movable relative said oil transfer/position feedback tube, said shuttle valve system operable to selectively communicate a hydraulic fluid from a high pressure source to said oil transfer/position feedback tube and from said oil transfer/position feedback tube to a reservoir. 12. A translational thrust system for a rotary-wing aircraft comprising: a propeller system which includes a propeller hub and a plurality of propeller blades which rotate about a propeller rotational axis transverse to a main rotor system axis of rotation; a propeller pitch change piston within said propeller hub, said propeller pitch change piston mechanically linked to said plurality of propeller blades; a mechanical-hydraulic control system in communication with said propeller system, said mechanical-hydraulic control system includes an oil transfer/position feedback tube mounted to said propeller pitch change piston, said propeller pitch change piston and said oil transfer/position feedback tube mounted for translational movement along said propeller rotational axis relative to said propeller hub to change a pitch of said plurality of propeller blades, said mechanical-hydraulic control system includes a shuttle valve system movable relative said oil transfer/position feedback tube, said shuttle valve system comprising: a shuttle valve housing mounted for translational movement with said oil transfer/position feedback tube; and a shuttle valve mounted within the shuttle valve housing to selectively communicate a hydraulic fluid from a high pressure source to said oil transfer/position feedback tube and from said oil transfer/position feedback tube to a reservoir. 13. A drive system for a rotary-wing aircraft comprising: a main rotor system which rotates about a main rotor system axis of rotation; a main gearbox to drive said main rotor system; and a translational thrust system driven by said main gearbox, said translational thrust system comprising: a propeller system which includes a propeller hub and a plurality of propeller blades which rotate about a propeller rotational axis transverse to said main rotor system axis of rotation; a propeller pitch change piston within said propeller hub, said propeller pitch change piston mechanically linked to said plurality of propeller blades; and a mechanical-hydraulic control system in communication with said propeller system, said mechanical-hydraulic control system includes an oil transfer/position feedback tube mounted to said propeller pitch change piston, said propeller pitch change piston and said oil transfer/position feedback tube mounted for translational movement along said propeller rotational axis relative to said propeller hub to change a pitch of said plurality of propeller blades, said propeller pitch change piston mounted to said oil transfer/position feedback tube for rotation relative thereto. 14. The drive system as recited in claim 13, wherein said main rotor system includes a coaxial contra-rotating rotor system. 15. The drive system as recited in claim 13, wherein said translational thrust system includes a pusher propeller. 16. The drive system as recited in claim 13, further comprising a propeller pitch controller in communication with a Fly-By-Wire (FBW) flight control system, said propeller pitch controller operable to adjust a pitch of said plurality of propeller blades. 17. The drive system as recited in claim 16, wherein said propeller pitch controller communicates with a sensor system which determines a translated position of said oil transfer/position feedback tube. 18. A method of controlling a translational thrust system of a rotary-wing aircraft comprising: (A) translating an oil transfer/position feedback tube and a propeller pitch change piston relative to a propeller hub along a propeller rotational axis transverse to a main rotor system axis of rotation to change a pitch of a propeller system, the oil transfer/position feedback tube mounted to the propeller pitch change piston, the propeller pitch change piston mounted to the oil transfer/position feedback tube for rotation relative thereto. 19. A method as recited in claim 18, further comprising the step of: (B) changing a pitch of the plurality of propeller blades independent of an RPM of the propeller system. 20. A method as recited in claim 18, wherein said step (A) further comprises: (B) controlling a valve system to translate the oil transfer/position feedback tube in response to a position sensor system which determines a translated position of said oil transfer/position feedback tube.
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이 특허에 인용된 특허 (10)
Lampeter Robert J. (Windsor CT) Duchesneau Jerome G. (Andover CT), Blade pitch change control system.
Leclercq, Maxime; Gemmati, Bernard; Veron, Philippe; Malburet, Francois, Hydraulic control valve, a device for adjusting blade pitch, and an aircraft provided with such a hydraulic control valve.
Couderc, Gérard; Chouteau, Mathilde; Biest, Romuald, System for controlling pitch variation of the blades of a propeller, a propeller, and an aircraft.
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