Aircraft drive wheel drive system with torque coupling clutch assembly
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-025/40
B60B-025/12
F16D-041/16
B60B-027/00
출원번호
US-0611100
(2015-01-30)
등록번호
US-9567069
(2017-02-14)
발명자
/ 주소
Cox, Isaiah W.
출원인 / 주소
Borealis Technical Limited
인용정보
피인용 횟수 :
2인용 특허 :
16
초록▼
An aircraft drive wheel drive system is provided with a torque coupling clutch assembly that transfers torque to a roller traction drive system actuating a non-engine drive means to drive an aircraft landing gear wheel and move the aircraft autonomously in a desired ground direction and at a desired
An aircraft drive wheel drive system is provided with a torque coupling clutch assembly that transfers torque to a roller traction drive system actuating a non-engine drive means to drive an aircraft landing gear wheel and move the aircraft autonomously in a desired ground direction and at a desired ground speed. The wheel drive system and clutch assembly are mounted completely within the wheel where the clutch assembly is selectively engaged to control torque transmission to the drive system, which selectively transfers actuating torque to the non-engine drive means. A preferred selectable one way clutch is adapted to controllably transfer torque to the wheel drive system and has both failsafe overrunning and selective engagement capability in one or both rotational directions so that torque required to drive the aircraft wheel and move the aircraft at a desired ground speed and direction is transferred only when required by aircraft operating conditions.
대표청구항▼
1. An aircraft drive wheel drive system designed to selectively transfer torque and drive an aircraft landing gear wheel to efficiently move an aircraft autonomously without reliance on aircraft engines or external vehicles during ground operations comprising: a. a wheel drive system assembly mounte
1. An aircraft drive wheel drive system designed to selectively transfer torque and drive an aircraft landing gear wheel to efficiently move an aircraft autonomously without reliance on aircraft engines or external vehicles during ground operations comprising: a. a wheel drive system assembly mounted completely within a space defined interior to a tire-supporting wall and between inboard and outboard walls of one or more aircraft nose landing gear wheels and operably connected to said one or more nose wheels to control forward and reverse rotation of said one or more nose wheels; andb. said wheel drive system assembly comprising an electric drive motor in driving and rotation powering contact with said one or more nose wheels to drive said one or more nose wheels at a desired speed and torque;a drive system in actuating and powering contact with said electric drive motor to actuate said electric drive motor to power said one or more nose wheels at said desired speed and torque; andan automatically or manually controllable clutch assembly supported completely and integrally within said defined space within said one or more nose wheels and coupled in selective engagement and disengagement torque transfer and actuating relationship to said drive system; wherein said clutch assembly comprises a selectable one-way clutch configured to selectively transfer or prevent transfer of torque comprises a through said wheel drive system assembly wherein said drive system comprises a roller traction drive system, and said selectable one-way clutch comprises a hydraulic or electromagnetic actuator in actuating communication with said selectable one-way clutch automatically or manually controllable to transfer an optimum drive torque to said roller traction drive system in response to a control force from said actuator. 2. An aircraft drive wheel drive system designed to drive an aircraft landing gear wheel and efficiently move an aircraft autonomously during ground operations comprising: a. one or more wheels rotatably mounted on an aircraft nose or main landing gear controllable to drive the aircraft autonomously during ground travel without reliance on aircraft engines or external vehicles; andb. a wheel drive system assembly mounted completely within said one or more wheels operably connected to said one or more wheels to control rotation of said one or more wheels, wherein said wheel drive system assembly comprises a drive motor in driving and rotation powering contact with said at least one wheel to drive said at least one wheel at a desired speed and torque; a drive system in actuating contact with said drive motor to activate said drive motor to power and drive said wheel at said desired speed and torque; and a clutch assembly coupled to transfer torque to said drive system and automatically or manually controllable to selectively engage and disengage said drive system into and out of said activating torque transfer contact with said drive motor;wherein said clutch assembly is supported integrally with said drive motor and said drive system completely within said one or more wheels and comprises a selectable one-way clutch coupled in selective drive torque transfer control relationship to said wheel drive system assembly, wherein said selectable one-way clutch comprises a plurality of coaxial rotating annular plates positioned to support and selectively engage a plurality of reverse and forward locking elements supported by at least one of said plates in response to a control force from a controllable actuator in automatic or manual actuating communication with said selectable one-way clutch. 3. The system of claim 2, wherein said plurality of reverse and forward locking elements comprise spring biased structures adapted to be movable into and out of engagement with corresponding recesses in one or more of said annular plates to selectively overrun or lock rotational movement of said one or more annular plates in a reverse or in a forward direction in response to said control force. 4. The system of claim 2, wherein said reverse and forward locking elements comprise rockers, struts, or pins. 5. The system of claim 2, wherein said selectable one-way clutch rotating annular plates and said locking elements are designed to withstand torque loads in excess of a determined maximum torque load for said aircraft drive wheel drive system and are made of materials designed for long term operation aircraft landing gear wheel environmental and operating conditions. 6. The system of claim 2, wherein said drive motor comprises a high phase order electric motor, said drive system comprises a roller traction drive system in actuating contact with said high phase order electric motor, and said selectable one-way clutch is automatically or manually controllably coupled in torque transfer relationship with said roller traction drive system and comprises a plurality of coaxial rotating annular plates supporting and selectively engaging a plurality of reverse and forward locking elements supported on at least one of said plates in response to a control force produced by a hydraulic or electromagnetic actuator, whereby an optimum drive torque is automatically or manually selectively transferred or not transferred from said selectable one-way clutch to said roller traction drive system. 7. The system of claim 6, wherein said selectable one-way clutch is automatically or manually controllable to prevent engagement of said reverse and forward locking elements in response to said control force so that said clutch is configured to be in an overrunning condition and unable to activate said roller traction drive system. 8. The system of claim 2, wherein said selectable one-way clutch comprises a failsafe mechanism operable to prevent transfer of torque to said drive system. 9. A method for selectively transferring torque required to drive an aircraft landing gear wheel to drive an aircraft autonomously without engines or external vehicles during ground operations only when the aircraft landing gear wheels may be safely driven, comprising: a. mounting a wheel drive system assembly mounted completely within the walls of one or more of an aircraft's nose or main landing gear wheels to control rotation of the landing gear wheels in a forward or a reverse direction to drive the aircraft;b. providing within each wheel drive system assembly an electric drive motor in torque transfer and powering contact with the landing gear wheels, a drive system in activating and torque transfer contact with the electric drive motor to activate said electric drive motor to power said wheel, and an automatically or manually actuatable and selectively engageable and disengageable clutch assembly comprising a selectable one-way clutch comprising a plurality of coaxial rotating plates supporting and selectively engaging, in response to a control force from a controllable actuator, a plurality of reverse and forward locking elements supported on at least one of the plates coupled in transfer torque actuating contact with the drive system; andc. automatically or manually actuating the selectable one-way clutch to selectively engage or disengage the drive system into or out of torque transfer contact with the electric drive motor to control rotation of the landing gear wheels in a desired forward or reverse direction or to prevent rotation of the landing gear wheels, as required to transfer an optimum torque only when the aircraft may be driven safely during ground operations. 10. The method of claim 9, further comprising providing within each wheel drive assembly a drive system comprising a roller traction drive system in activating torque transfer contact with the electric drive motor; and automatically or manually controlling torque transfer from the drive system to the electric drive motor and activating the electric drive motor to move the landing gear wheels in the desired forward or reverse direction at a desired speed and torque when the aircraft is moving on a ground surface, and automatically or manually preventing torque transfer to the landing gear wheels through each wheel drive assembly when the aircraft is taking off, landing, or in the air, or when the wheel drive system assembly may not be operated safely to drive the aircraft safely during ground operations. 11. The method of claim 9, further comprising providing the selectable one-way clutch with an automatically or manually actuatable integral failsafe overrunning capability and preventing engagement and activation of the drive system into torque transfer contact with the electric drive and controlling or preventing rotation of the landing gear wheels when the failsafe overrunning capability is actuated to prevent engagement of the selectable one-way clutch and torque transfer to the drive system and the electric drive motor when the aircraft is taking off, landing, or in the air, or when wheel drive system assembly may not be operated safely or the aircraft may not be safely driven on the ground. 12. The method of claim 9, further comprising arranging the plurality of reverse and forward locking elements in a plurality of engagement and disengagement combinations to selectively control torque transfer when the wheel drive assembly is powered to move the aircraft in the desired forward and reverse directions at a desired speed and to prevent torque transfer when the aircraft is stopped.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (16)
Christensen, Donald J.; Langston, Todd; Charles, David Lane; Velasquez, Rudy, Aircraft electric taxi system with friction actuated, bi-directional clutch.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.