Apparatus for moving a control surface
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
UP-0603360
(2006-11-21)
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등록번호 |
US-7641145
(2010-02-11)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
Tarolli, Sundheim, Covell & Tummino LLP
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인용정보 |
피인용 횟수 :
3 인용 특허 :
5 |
초록
▼
An apparatus for use in moving a control surface during operation of an aircraft includes a flexible drive shaft to be connected with an actuator assembly by a coupling assembly. Operation of the actuator assembly operates a force transmission apparatus to move a control surface on an aircraft. The
An apparatus for use in moving a control surface during operation of an aircraft includes a flexible drive shaft to be connected with an actuator assembly by a coupling assembly. Operation of the actuator assembly operates a force transmission apparatus to move a control surface on an aircraft. The coupling assembly includes an input member connected with the flexible drive shaft and an output member which may be connected with the actuator assembly. A plurality of balls interconnect the input and output members and are rotatable to accommodate relative movement between the input and output members.
대표청구항
▼
Having described the invention, the following is claimed: 1. An apparatus for use in moving a control surface during operation of an aircraft, said apparatus comprising an actuator assembly which is connected with the control surface by a force transmission apparatus, a flexible drive shaft which i
Having described the invention, the following is claimed: 1. An apparatus for use in moving a control surface during operation of an aircraft, said apparatus comprising an actuator assembly which is connected with the control surface by a force transmission apparatus, a flexible drive shaft which is rotatable about a longitudinal central axis of said flexible drive shaft, and a coupling assembly which interconnects said flexible drive shaft and said actuator assembly, said coupling assembly includes an input member connected with said flexible drive shaft, an output member connected with said actuator assembly, and a plurality of balls which interconnect said input and output members and are rotatable to accommodate relative movement between said input and output members, said actuator assembly includes a worm gear which is connected with said input member of said coupling assembly and is rotated by said input member of said coupling assembly upon rotation of said flexible drive shaft and a worm wheel which is disposed in meshing engagement with said worm gear, said worm wheel being rotatable under the influence of force transmitted from said flexible drive shaft through said coupling assembly and said worm gear to said worm wheel to actuate said force transmission apparatus to move the control surface. 2. An apparatus as set forth in claim 1 wherein a first one of said input and output members includes a circular wall which extends around a second one of said input and output members, said wall of said first one of said input and output members at least partially defines a first groove which extends from a first end portion of said wall to a second end portion of said wall, said second one of said input and output members having a first end portion which is telescopically received in a chamber which is at least partially defined by said wall of said first one of said input and output members, said first end portion of said second one of said input and output members at least partially defining a second groove, said outer surface of at least one of said balls of said plurality of balls being disposed in engagement with said first and second grooves. 3. An apparatus as set forth in claim 1 wherein said flexible drive shaft is formed by layers of wound wire, said flexible drive shaft being enclosed by a casing which is connected with a housing for said actuator assembly. 4. An apparatus as set forth in claim 1 further including a connector member which extends around an end portion of said flexible drive shaft and is at least partially enclosed by said input member, said connector member being retained against rotation relative to said flexible drive shaft and said input member to enable said connector member to transmit torque between said flexible drive shaft and said input member. 5. An apparatus as set forth in claim 1 wherein said worm gear is movable along a central axis of said coupling assembly upon occurrence of excessive resistance to movement of the aircraft control surface by said force transmission apparatus, said output coupling member being movable along the central axis of said coupling assembly under the influence of force transmitted from said worm gear to said output coupling member upon movement of said worm gear along the central axis of said coupling assembly. 6. An apparatus as set forth in claim 5 wherein said plurality of balls roll relative to at least one of said input and output members of said coupling assembly upon movement of said output coupling member along the central axis of said coupling assembly. 7. An apparatus as set forth in claim 1 wherein said worm gear is axially movable by said output coupling member along a central axis of said coupling assembly upon occurrence of excessive resistance to movement of the aircraft control surface, said output coupling member being movable along the central axis of said coupling assembly under the influence of force transmitted from said worm gear to said output coupling member upon movement of said worm gear along the central axis of said coupling assembly. 8. An apparatus as set forth in claim 7 wherein said plurality of balls roll relative to at least one of said input and output members of said coupling assembly upon movement of said output coupling member along the central axis of said coupling assembly. 9. An apparatus as set forth in claim 1 wherein said actuator assembly includes a ball nut which is connected with said worm wheel and said force transmission apparatus, said force transmission apparatus includes an externally threaded member which is engaged by said ball nut. 10. An apparatus as set forth in claim 1 wherein said actuator assembly includes a brake assembly which is connected with said worm gear and is operable to retard rotation of said worm gear upon occurrence of excessive resistance to movement of the aircraft control surface by said force transmission apparatus. 11. An apparatus for use in moving a control surface during operation of an aircraft, said apparatus comprising a flexible drive shaft which is rotatable about a longitudinal central axis of said flexible drive shaft to transmit power to operate an actuator assembly connected with the aircraft control surface by a force transmission apparatus to move the control surface relative to the aircraft, and a coupling assembly having input and output force transmitting members which are in interconnected for rotation about a drive axis by a plurality of balls, each of said balls of said plurality of balls having an outer surface which is disposed in engagement with a surface on said input force transmitting member and a surface on said output force transmitting member, said input force transmitting member being directly connected with and rotatable with said flexible drive shaft about said drive axis during transmission of power to operate the actuator assembly and force transmission apparatus to move the control surface relative to the aircraft, said input force transmitting member being retained against movement along said drive axis and being effective to apply force against said plurality of balls during transmission of power to operate the actuator assembly and force transmission apparatus to move the control surface relative to the aircraft, said output force transmitting member being connectable with the actuator assembly and rotatable about said drive axis under the influence of force transmitted from said input force transmitting member to said output force transmitting member through said plurality of balls during transmission of power to operate the actuator assembly and force transmission apparatus to move the control surface relative to the aircraft, said output force transmitting member being movable relative to said input force transmitting member along said drive axis under the influence of force transmitted from the actuator assembly upon occurrence of excessive resistance to movement of the aircraft control surface by the force transmission apparatus. 12. An apparatus as set forth in claim 11 wherein said flexible drive shaft is formed by layers of wound wire, said flexible drive shaft being enclosed by casing which is connected with a housing for the actuator assembly. 13. An apparatus as set forth in claim 11 wherein a first one of said input and output members includes a circular wall which extends around a second one of said input and output members, said wall of said first one of said input and output members at least partially defines a first groove which extends from a first end portion of said wall to a second end portion of said wall, said second one of said input and output members having a first end portion which is telescopically received in a chamber which is at least partially defined by said wall of said first one of said input and output members, said first end portion of said second one of said input and output members at least partially defining a second groove, said outer surface of at least one of said balls of said plurality of balls being disposed in engagement with said first and second grooves.
이 특허에 인용된 특허 (5)
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Shaheen, Milad A.; Dreher, Robert V., Actuator for aircraft stabilizers with a failure responsive lock control mechanism.
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Perni, Federico; Capolungo, Sandro; Pizzoni, Luciano, Ball screw actuator for aircraft control surfaces.
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Teske Duane R. (Rockford IL) Senasack ; Jr. Henry E. (Annapolis MD) Wilkins Mark (Burke VA), Ballscrew actuator.
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Farley Brian,GBX ; Morgan Antony,GBX ; Mountney Arthur Derek,GBX ; Matthews Timothy Robert,GBX, Flight control surface actuation system.
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Richard Simon Capewell GB; Richard John McKay GB, Rotary actuator and system.
이 특허를 인용한 특허 (3)
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Elliot, Nicholas; Didey, Arnaud, Aircraft steering actuator.
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Elliott, Nicholas; Didey, Arnaud, Linear actuator.
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Van Zyl, Louwrens Hermias, Wing control system.
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