Actuator device for flight control surface, flight control surface of aircraft, and aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/36
B64C-009/02
B64C-009/00
출원번호
US-0105763
(2013-12-13)
등록번호
US-9663221
(2017-05-30)
우선권정보
JP-2012-282530 (2012-12-26)
발명자
/ 주소
Ishihara, Kenya
출원인 / 주소
MITSUBISHI AIRCRAFT CORPORATION
대리인 / 주소
Pearne & Gordon LLP
인용정보
피인용 횟수 :
0인용 특허 :
17
초록▼
To provide an actuator device for a flight control surface which can reduce a stress applied to the flight control surface when one of two actuators is operated. The present invention relates to a hydraulically-operated actuator device 30 which drives a flight control surface of an aircraft 1, inclu
To provide an actuator device for a flight control surface which can reduce a stress applied to the flight control surface when one of two actuators is operated. The present invention relates to a hydraulically-operated actuator device 30 which drives a flight control surface of an aircraft 1, including a first actuator 31A that is provided with a first piston rod 39A, and drives an aileron body 11; a second actuator 31B that is provided with a second piston rod 39B, and drives the aileron body 11 when the function of the first actuator 31A is lost or reduced; and a single second connection fitting 41 to which the first piston rod 39A and the second piston rod 39B are both connected, wherein the first actuator 31A and the second actuator 31B are connected to the aileron body 11 via the second connection fitting 41.
대표청구항▼
1. An actuator device for a flight control surface which drives a flight control surface of an aircraft, the actuator device comprising: a first actuator that comprises a first output section, and drives the flight control surface;a second actuator that comprises a second output section, and drives
1. An actuator device for a flight control surface which drives a flight control surface of an aircraft, the actuator device comprising: a first actuator that comprises a first output section, and drives the flight control surface;a second actuator that comprises a second output section, and drives the flight control surface instead of the first actuator; anda connection fitting to which each of the first output section and the second output section is connected,wherein the first actuator and the second actuator are connected to the flight control surface via the connection fitting,a first link member, one end of which is rotatably supported on the first actuator and another end of which is rotatably connected to the connection fitting about a rotational axis of the control surface, anda second link member, one end of which is rotatably supported on the second actuator and another end of which is rotatably connected to the connection fitting about the rotational axis of the control surface,wherein in the first actuator, the first output section is rotatably connected to the connection fitting about an axis offset from the rotational axis of the control surface where the first link member and the second link member are rotatably connected, andin the second actuator, the second output section is rotatably connected to the connection fitting about the axis offset from the rotational axis of the control surface,wherein actuation of the first actuator or the second actuator causes the connection fitting to pivot about the rotational axis of the control surface. 2. The actuator device for a flight control surface according to claim 1, wherein each of the first actuator and the second actuator comprises a hydraulic cylinder as a main constituent element. 3. The actuator device for a flight control surface according to claim 2, wherein the hydraulic cylinder of the first actuator comprises a piston rod as the first output section, and the hydraulic cylinder of the second actuator comprises a piston rod as the second output section. 4. The actuator device for a flight control surface according to claim 2, wherein each of the first link member and the second link member has a Y shape,a distal end on a bifurcated side of each of the first link member and the second link member is rotatably supported on an end portion of the hydraulic cylinder, and a distal end on the opposite side of each of the first link member and the second link member is rotatably supported on the connection fitting. 5. The actuator device for a flight control surface according to claim 1, wherein hydraulic oil is supplied to the first actuator and the second actuator from separate hydraulic systems. 6. The actuator device for a flight control surface according to claim 1, wherein the flight control surface is an aileron. 7. The actuator device for a flight control surface according to claim 1, wherein both of the first actuator and the second actuator are provided on the same flight control surface and are located in a longitudinal direction of the flight control surface. 8. The actuator device for a flight control surface according to claim 7, wherein the first actuator and the second actuator are located near the center of the flight control surface. 9. The actuator device for a flight control surface according to claim 1, wherein hinges are provided on the flight control surface so as to be located near the first actuator and the second actuator and in a longitudinal direction of the flight control surface. 10. A flight control surface of an aircraft which is driven by the actuator device according to claim 1. 11. An aircraft comprising a flight control surface driven by the actuator device according to claim 1. 12. The aircraft according to claim 11, wherein the flight control surface is an aileron. 13. The actuator device for a flight control surface according to claim 1, wherein the first actuator and the second actuator are separately hinged to the connection fitting. 14. An actuator device for a flight control surface which drives a flight control surface of an aircraft, the actuator device comprising: a first actuator that comprises a first output section, and drives the flight control surface;a second actuator that comprises a second output section, and drives the flight control surface instead of the first actuator; anda connection fitting to which the first output section and the second output section are both connected,wherein the first actuator and the second actuator are connected to the flight control surface via the connection fitting,wherein each of the first actuator and the second actuator comprises a hydraulic cylinder as a main constituent element,wherein the hydraulic cylinder of the first actuator comprises a piston rod as the first output section, and the hydraulic cylinder of the second actuator comprises a piston rod as the second output section, andwherein the connection fitting has a substantially C-shaped section, and comprises supporting members,one of the supporting members supports the another end of the first link member and one end of the piston rod as the first output section,another of the supporting members supports the another end of the second link member and one end of the piston rod as the second output section.
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이 특허에 인용된 특허 (17)
Fitzgibbon Thomas F. (Long Beach CA) Hamilton Paul U. (Palos Verdes Est. CA), Actuating system for aircraft wing slat and flap panels.
Wingett, Paul T.; Potter, Calvin C.; Hanlon, Casey; Benson, Dwayne M., Flight control surface actuation system with redundantly configured and lockable actuator assemblies.
Andreani, Luc, Lateral coupling device for holding and guiding at least one aerodynamic body relative to the main wing of an aircraft, airfoil and aircraft with such a lateral coupling device.
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