[특허]Maintaining drive system alignment in tiltrotor aircraft

Bell Helicopter Textron Inc.

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특허 상세정보

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Maintaining drive system alignment in tiltrotor aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-029/00 B64F-005/40
출원번호	US-0417113 (2017-01-26)
등록번호	US-9663225 (2017-05-30)
발명자 / 주소	Kooiman, James Everett Decker, George Ryan Baines, Andrew G. Bockmiller, David R. Kohler, Erick Wayne
출원인 / 주소	Bell Helicopter Textron Inc.
대리인 / 주소	Lawrence Youst PLLC
인용정보	피인용 횟수 : 3 인용 특허 : 31

초록
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A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.

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1. A drive system for a tiltrotor aircraft including an airframe and having a helicopter mode and an airplane mode, the drive system comprising: a first gearbox rotatably coupled to the airframe and having an input gear, the first gearbox rotatable about a longitudinal axis to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode;a second gearbox having an output gear, the second gearbox extending generally normal to the longitudinal axis of the first gearbox;a common shaft configured to transfer torque from the output gear of the second gearbox to the input gear of the first gearbox, the common shaft rotatable about the longitudinal axis; anda support assembly coupling the second gearbox to the airframe, the support assembly including a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox relative to the longitudinal axis and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox relative to the longitudinal axis;wherein, the first radial growth degree of freedom is not parallel with the second radial growth degree of freedom; andwherein, the support assembly maintains the output gear of the second gearbox in substantial collinear alignment with the input gear of the first gearbox. 2. The drive system as recited in claim 1 wherein the fixed joint further comprises a bolted connection. 3. The drive system as recited in claim 1 wherein the first directional reacting joint further comprises an A-frame connector having spherical elements generally normal to the first radial growth degree of freedom of the second gearbox. 4. The drive system as recited in claim 1 wherein the second directional reacting joint further comprises an A-frame connector having spherical elements generally normal to the second radial growth degree of freedom of the second gearbox. 5. The drive system as recited in claim 1 wherein the fixed joint, the first directional reacting joint and the second directional reacting joint provide lateral support to the second gearbox. 6. The drive system as recited in claim 1 wherein the fixed joint and the first directional reacting joint provide support to the second gearbox in a direction generally parallel to the second radial growth degree of freedom. 7. The drive system as recited in claim 1 wherein the fixed joint and the second directional reacting joint provide support to the second gearbox in a direction generally parallel to the first radial growth degree of freedom. 8. The drive system as recited in claim 1 wherein the first radial growth degree of freedom further comprises a first thermal growth degree of freedom and wherein the second radial growth degree of freedom further comprises a second thermal growth degree of freedom. 9. The drive system as recited in claim 1 wherein the first radial growth degree of freedom is generally normal to the second radial growth degree of freedom. 10. The drive system as recited in claim 1 wherein the first radial growth degree of freedom is generally in a fore/aft direction and wherein the second radial growth degree of freedom is generally in a vertical direction. 11. The drive system as recited in claim 1 wherein the support assembly maintains the output gear of the second gearbox in substantial collinear alignment with the input gear of the first gearbox throughout thermal expansion cycles of the second gearbox. 12. A tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft comprising: an airframe including a fuselage and a wing;an engine supported by the airframe proximate an outboard end of the wing;a pylon assembly coupled to the airframe inboard of the engine and above the wing, the pylon assembly including a spindle gearbox having an input gear, a mast and a proprotor assembly operable to rotate with the mast, the spindle gearbox rotatable about a conversion axis to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode;a fixed gearbox operably coupled to the engine and having an output gear, the fixed gearbox extending generally normal to the conversion axis of the spindle gearbox;a common shaft configured to transfer torque from the output gear of the fixed gearbox to the input gear of the spindle gearbox, the common shaft rotatable about the conversion axis; anda support assembly coupling the fixed gearbox to the airframe, the support assembly including a fixed joint proximate the conversion axis, a first directional reacting joint remote from the conversion axis providing a first radial growth degree of freedom to the fixed gearbox relative to the conversion axis and a second directional reacting joint remote from the conversion axis providing a second radial growth degree of freedom to the fixed gearbox relative to the longitudinal axis;wherein, the first radial growth degree of freedom is not parallel with the second radial growth degree of freedom; andwherein, the support assembly maintains the output gear of the fixed gearbox in substantial collinear alignment with the input gear of the spindle gearbox. 13. The tiltrotor aircraft as recited in claim 12 wherein the fixed joint further comprises a bolted connection, wherein the first directional reacting joint further comprises an A-frame connector having spherical elements generally normal to the first radial growth degree of freedom of the fixed gearbox and wherein the second directional reacting joint further comprises an A-frame connector having spherical elements generally normal to the second radial growth degree of freedom of the fixed gearbox. 14. The tiltrotor aircraft as recited in claim 12 wherein the fixed joint, the first directional reacting joint and the second directional reacting joint provide lateral support to the fixed gearbox, wherein the fixed joint and the first directional reacting joint provide support to the fixed gearbox in a direction generally parallel to the second radial growth degree of freedom and wherein the fixed joint and the second directional reacting joint provide support to the fixed gearbox in a direction generally parallel to the first radial growth degree of freedom. 15. The tiltrotor aircraft as recited in claim 12 wherein the first radial growth degree of freedom further comprises a first thermal growth degree of freedom, wherein the second radial growth degree of freedom further comprises a second thermal growth degree of freedom and wherein the support assembly maintains the output gear of the fixed gearbox in substantial collinear alignment with the input gear of the spindle gearbox throughout thermal expansion cycles of the fixed gearbox. 16. The tiltrotor aircraft as recited in claim 12 wherein the first radial growth degree of freedom is generally in a fore/aft direction and wherein the second radial growth degree of freedom is generally in a vertical direction. 17. A method of maintaining substantial collinear alignment throughout thermal expansion cycles of a drive system of a tiltrotor aircraft having a helicopter mode and an airplane mode, the method comprising: rotatably coupled a first gearbox to an airframe such that the first gearbox is rotatable about a longitudinal axis to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode;positioning a second gearbox generally normal to the longitudinal axis of the first gearbox;transferring torque from an output gear of the second gearbox to an input gear of the first gearbox with a common shaft rotatable about the longitudinal axis; andcoupling the second gearbox to the airframe with a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox relative to the longitudinal axis and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox relative to the longitudinal axis, thereby maintaining the output gear of the second gearbox in substantial collinear alignment with the input gear of the first gearbox throughout thermal expansion cycles of the second gearbox. 18. The method as recited in claim 17 further comprising providing lateral support to the second gearbox with the fixed joint, the first directional reacting joint and the second directional reacting joint. 19. The method as recited in claim 17 further comprising providing support to the second gearbox in a direction generally parallel to the second radial growth degree of freedom with the fixed joint and the first directional reacting joint. 20. The method as recited in claim 17 further comprising providing support to the second gearbox in a direction generally parallel to the first radial growth degree of freedom with the fixed joint and the second directional reacting joint.

이 특허에 인용된 특허 (31)

이 특허를 인용한 특허 피인용횟수: 3

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Maintaining drive system alignment in tiltrotor aircraft

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이 특허에 인용된 특허 (31)

이 특허를 인용한 특허 피인용횟수: 3

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Maintaining drive system alignment in tiltrotor aircraft

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이 특허에 인용된 특허 (31)

이 특허를 인용한 특허 피인용횟수: 3

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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