Propulsive anti-torque nozzle system with external rotating sleeve for a rotorcraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-015/00
B64C-027/82
출원번호
US-0579002
(2010-11-12)
등록번호
US-8636242
(2014-01-28)
국제출원번호
PCT/US2010/056557
(2010-11-12)
§371/§102 date
20120814
(20120814)
국제공개번호
WO2012/064343
(2012-05-18)
발명자
/ 주소
Smith, Dudley E.
출원인 / 주소
Textron Innovations Inc.
대리인 / 주소
Walton, James E.
인용정보
피인용 횟수 :
2인용 특허 :
3
초록▼
The system of the present application includes a system duct in fluid communication with a tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout. The system further includes an anti-torque nozzle exteriorly proximate to the anti-torque cutout a
The system of the present application includes a system duct in fluid communication with a tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout. The system further includes an anti-torque nozzle exteriorly proximate to the anti-torque cutout and a pro-torque nozzle exteriorly proximate to the pro-torque cutout. A rotating sleeve is configured to selectively allow airflow into at least one of the anti-torque nozzle and the pro-torque nozzle. A thrust nozzle is in fluid communication with the system duct. An upper clamshell and a lower clamshell are each configured to selectively control airflow in the thrust nozzle.
대표청구항▼
1. A propulsive anti-torque system for an aircraft, the propulsive anti-torque system comprising: a system duct in fluid communication with a tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout;an anti-torque nozzle exteriorly proximate to th
1. A propulsive anti-torque system for an aircraft, the propulsive anti-torque system comprising: a system duct in fluid communication with a tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout;an anti-torque nozzle exteriorly proximate to the anti-torque cutout;a pro-torque nozzle exteriorly proximate to the pro-torque cutout;a rotating sleeve configured to selectively allow airflow into at least one of the anti-torque nozzle and the pro-torque nozzle;a thrust nozzle in fluid communication with the system duct;an upper clamshell and a lower clamshell, each selectively controlled to contribute to pitch control and forward thrust, each controlled by a separate actuator so as to operate asymmetrically to alter the airflow through the system duct, the upper clamshell and lower clamshell having a curved shaped concaved to the flow of air so as to generate an upward thrust vector and a downward thrust vector. 2. The propulsive anti-torque system according to claim 1, wherein the rotating sleeve is concentric to the system duct. 3. The propulsive anti-torque system according to claim 1, wherein the airflow through the thrust nozzle produces a forward thrust vector on the aircraft. 4. The propulsive anti-torque system according to claim 1, wherein the airflow through the anti-torque nozzle produces an anti-torque vector, thereby producing a torque on the aircraft. 5. The propulsive anti-torque system according to claim 1, wherein the airflow through the pro-torque nozzle produces a pro-torque vector, thereby producing a torque on the aircraft. 6. The propulsive anti-torque system according to claim 1, wherein the airflow through the anti-torque nozzle and the thrust nozzle produces a resultant force which is a combination of an anti-torque vector and a thrust vector. 7. The propulsive anti-torque system according to claim 1, wherein the airflow is pressurized by an engine and a fan. 8. The propulsive anti-torque system according to claim 1, wherein the anti-torque nozzle comprises: at least one anti-torque vane for directing the airflow in an anti-torque producing direction. 9. The propulsive anti-torque system according to claim 1, wherein the pro-torque nozzle comprises: at least one pro-torque vane for directing the airflow in a pro-torque producing direction. 10. The propulsive anti-torque system according to claim 1, wherein the rotating sleeve is exterior to the system duct. 11. The propulsive anti-torque system according to claim 1, wherein the upper clamshell and the lower clamshell are configured to be actuated independently. 12. The propulsive anti-torque system according to claim 1, wherein the thrust nozzle is configured to produce an upward thrust vector when the lower clamshell is closed and the upper clamshell is open, thereby producing a pitching up moment on the aircraft. 13. The propulsive anti-torque system according to claim 1, wherein the thrust nozzle is configured to produce an downward thrust vector when the lower clamshell is open and the upper clamshell is closed, thereby producing a pitching down moment on the aircraft. 14. An aircraft comprising: an engine which provides power to a main rotor system;a fan;a tailboom duct that acts as a conduit to provide airflow to a propulsive anti-torque system, the airflow being a mixture of compressed air from the fan and exhaust from the engine; anda propulsive anti-torque system located near an aft end of the tailboom, the propulsive anti-torque system comprising: a system duct in fluid communication with the tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout;an anti-torque nozzle exterior and proximate to the anti-torque cutout;a pro-torque nozzle exterior and proximate to the pro-torque cutout;a rotating sleeve configured to selectively allow airflow into at least one of the anti-torque nozzle and the pro-torque nozzle;a thrust nozzle in fluid communication with the system duct; andan upper clamshell and a lower clamshell, each selectively controlled to contribute to pitch control and forward thrust, each controlled by a separate actuator so as to operate asymmetrically to alter the airflow through the system duct, the upper clamshell and lower clamshell having a curved shaped concaved to the flow of air so as to generate an upward thrust vector and a downward thrust vector. 15. The aircraft according to claim 14, wherein the airflow through the thrust nozzle produces a forward thrust vector on the aircraft. 16. The aircraft according to claim 14, wherein the airflow through the anti-torque nozzle produces an anti-torque vector, thereby producing a torque on the aircraft. 17. The aircraft according to claim 14, wherein the airflow through the pro-torque nozzle produces a pro-torque vector, thereby producing a torque on the aircraft. 18. The aircraft according to claim 14, wherein the airflow through the anti-torque nozzle and the thrust nozzle produces a resultant force which is a combination of an anti-torque vector and a thrust vector. 19. The aircraft according to claim 14, wherein the airflow is pressurized by an engine and a fan.
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이 특허에 인용된 특허 (3)
Munski Michael S. (44052 Fine St. Lancaster CA 93536), Helicopter antitorque auxiliary propulsion system.
Pantalone, III, Joseph; Chapkovich, III, John S.; Devito, Ashley; Eller, Erez, Rotary wing aircraft having collocated exhaust duct and propeller shaft.
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