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A drive system for rotating a wheel of a landing gear

A drive system, transmission error technology, applied in aircraft indicating devices, registration/indicating vehicle operation, machine gear/transmission mechanism testing, etc., can solve problems such as unknown drive system damage and vibration

Inactive Publication Date: 2019-09-03
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] However, it is not known how much vibration is actually induced in either such arrangement, or an indication of the damage any transmission error would cause to the drive system

Method used

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  • A drive system for rotating a wheel of a landing gear
  • A drive system for rotating a wheel of a landing gear
  • A drive system for rotating a wheel of a landing gear

Examples

Experimental program
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Embodiment Construction

[0050] figure 1 A perspective view of an aircraft main landing gear 10 comprising a drive system 20 according to a first embodiment of the invention is shown.

[0051] The aircraft landing gear 10 comprises a landing gear leg 13 , a shaft 12 and a wheel 11 mounted in a rotatable manner on the shaft 12 . A drive system 20 for rotating the wheels 11 is attached below the undercarriage legs 13 . The drive system 20 includes a drive pinion roller gear 24, a motor 21 operable to rotate the drive pinion roller gear 24 via a gearbox 22 and a gearbox output shaft 23, a driven chain sprocket 24, and a driven sprocket gear 25. A wheel gear 25 is attached to the wheel 11 so as to be able to rotate the wheel 11 . The drive path from the motor 21 to the wheels 11 is defined to include a gearbox 22 , a gearbox output shaft 23 , a drive pinion roller gear 24 and a driven sprocket gear 25 .

[0052] The drive system has figure 1 In the drive configuration shown in FIG. 1 , the drive pinio...

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PUM

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Abstract

The present invention provides a drive system (20,20') for rotating a wheel (11,11') of an aircraft landing gear (10,10') comprising a drive element (24,24'); a motor (21,21') operable to rotate the drive element, and a driven gear (25,25') adapted to be attached to the wheel. The the drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, wherein the drive system further comprises a transmission error measurement apparatus (30, 40), the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration. These measurements can be taken by torque, speed, or vibration sensors. The measurement data provides an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear. This indication can be used to decide on a maintenance or repair schedule for the drive system. The invention also provides an aircraft 100 and a method of providing an indication of a transmission error in a drive system.

Description

technical field [0001] The present disclosure relates to drive systems for rotating wheels of aircraft landing gear. [0002] The invention relates to a drive system for rotating wheels of aircraft landing gear. More particularly, but not exclusively, the present invention relates to a drive system for rotating a wheel of an aircraft landing gear, the drive system comprising a drive element, a motor and a driven gear, the motor being operable to rotate the drive element, the slave A driven gear is adapted to be attached to the wheel to enable rotation of the wheel, wherein the drive system has a drive configuration in which a drive element is engageable with the driven gear to drive the driven gear. [0003] The invention also relates to an aircraft and a method of providing an indication of a transmission error in a drive system for rotating the wheels of the aircraft's landing gear. Background technique [0004] Transmission errors are caused by the drive element and dri...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/34B64F5/60
CPCB64C25/34B64F5/60B64C25/405F16H57/01B64D2045/0085F16H55/10Y02T50/80B64C25/40B64D45/00G07C5/006G07C5/08F16D3/065F16D3/185F16H1/24F16H1/00G07C5/0841G07C5/004G07C5/085G07C5/008G07C5/02G01M13/02G07C5/0808G07C5/0816
Inventor 尼古拉斯·克兰阿诺·迪代
Owner AIRBUS OPERATIONS GMBH