Augmenting flight control surface actuation system and method
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/36
출원번호
US-0303271
(2002-11-25)
발명자
/ 주소
Krantz, Richard M.
출원인 / 주소
The Boeing Company
대리인 / 주소
Harness Dickey & Pierce P.L.C.
인용정보
피인용 횟수 :
15인용 특허 :
5
초록▼
Apparatus for providing actuation power to an aircraft flight control surface. The apparatus includes a first actuator and a second actuator, where the second actuator has a bypass mode and an assist mode. The mode of the second actuator is determined by an internal differential pressure across the
Apparatus for providing actuation power to an aircraft flight control surface. The apparatus includes a first actuator and a second actuator, where the second actuator has a bypass mode and an assist mode. The mode of the second actuator is determined by an internal differential pressure across the first actuator. The apparatus further includes a mode select valve for selecting between the bypass mode and the assist mode for the second actuator, and a solenoid valve that when energized causes the mode select valve to select the other mode for the second actuator. When the second actuator is in the bypass mode, the first actuator provides the actuation power for the aircraft flight control surface. But, when the second actuator is in the assist mode, both the first and second actuators provide the actuation power for the aircraft flight control surface. Accordingly, the apparatus allows the flight control surface to be operated in a more efficient manner with less hydraulic flow being required.
대표청구항▼
Apparatus for providing actuation power to an aircraft flight control surface. The apparatus includes a first actuator and a second actuator, where the second actuator has a bypass mode and an assist mode. The mode of the second actuator is determined by an internal differential pressure across the
Apparatus for providing actuation power to an aircraft flight control surface. The apparatus includes a first actuator and a second actuator, where the second actuator has a bypass mode and an assist mode. The mode of the second actuator is determined by an internal differential pressure across the first actuator. The apparatus further includes a mode select valve for selecting between the bypass mode and the assist mode for the second actuator, and a solenoid valve that when energized causes the mode select valve to select the other mode for the second actuator. When the second actuator is in the bypass mode, the first actuator provides the actuation power for the aircraft flight control surface. But, when the second actuator is in the assist mode, both the first and second actuators provide the actuation power for the aircraft flight control surface. Accordingly, the apparatus allows the flight control surface to be operated in a more efficient manner with less hydraulic flow being required. s at least one of an aircraft actuation system, an aircraft fuel tank and an aircraft storage container. 5. An aircraft flight control system according to claim 1 in which the portion of the aircraft mass includes more than one mass element, and in which the bearings permit independent relative movement between each mass element and the lift generating means. 6. An aircraft flight control system according to claim 1 in which the actuation means comprise linear electrical actuators. 7. An aircraft flight control system according to claim 1 in which the aerodynamic lift generating means comprise a pair of wings each having a variable wing area. 8. An aircraft flight control system according to claim 7 in which each wing comprises a first wing portion which is fixed relative to the body of the aircraft, a second wing portion which is mounted to the first wing portion by means of bearings so as to be extendable and retractable relative thereto, and actuation means for extending and retracting the second wing portion. 9. A method of flight control in an aircraft, said aircraft having a mass and including an aerodynamic lift generating means, comprising the Steps of: mounting a portion of said aircraft mass on a support, mounting said support for movement in lateral and longitudinal directions relative to said lift generating means, and moving the support and the portion of said aircraft mass In said lateral and longitudinal directions relative to the aerodynamic lift generating means for effecting flight control of said aircraft. 10. A method according to claim 9 which the aerodynamic lift generating means comprise a pair of wings, and including the further step of varying the wing area for controlling the lift. 11. An aircraft flight control system, said aircraft having a body and including aerodynamic lift generating means and at least one engine, said engine having a thrust line, said flight control system comprising: a portion of said lift generating means mounted to the aircraft, bearings permitting relative movement between the aircraft body and said portion of the lift generating means, said movement in lateral and longitudinal directions in a plane substantially parallel to said thrust line, and actuation means for moving said portion of said lift generating means relative to said aircraft body in said lateral and longitudinal directions in said plane for effecting flight control of said aircraft. 12. An aircraft flight control system according to claim 11 wherein the bearings comprise liner bearings. 13. An aircraft flight control system according to claim 11 in which the actuation means comprise linear electrical actuators. 14. An aircraft flight control system according to claim 11 in which the aerodynamic lift generating means comprise a pair of wings each wing having a variable wing area. 15. An aircraft flight control system according to claim 14 in which each wing comprises a first wing portion which is fixed relative to the body of the aircraft, a second wing portion which is mounted to the first wing portion by means of bearings so as to be extendable and retractable relative thereto, and actuation means for extending and retracting the second wing portion. 16. A method of flight control in an aircraft, said aircraft having a body and including an aerodynamic lift generating means and at least one engine, said engine having a thrust line, comprising the steps of: mounting a portion of said lift generating means to the aircraft body, mounting said portion of said lift generating means for movement in lateral and longitudinal directions in a Diane substantially parallel to said thrust line relative to said aircraft body, and moving the portion of said lift generating means in said lateral and longitudinal directions in said plane relative to said aircraft body. 17. A method according to claim fin which the aerodynamic lift generating means comprise a pair of wings, and including the further step of varying the wing area for controlling the lift.
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