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Aircraft landing gear steering system

A landing gear and steering system technology, applied in the direction of landing gear, transmission, mechanical steering gear, etc., can solve the problems of increasing the leakage of hydraulic fluid, increasing the weight and complexity of the aircraft steering system, and achieve the effect of a compact steering device

Inactive Publication Date: 2010-03-10
TRIUMPH ACTUATION SYST UK
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

however, such hydraulic accumulators and valves not only add weight and complexity to some conventional aircraft steering systems, but also increase the likelihood of hydraulic fluid leaks

Method used

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  • Aircraft landing gear steering system
  • Aircraft landing gear steering system
  • Aircraft landing gear steering system

Examples

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Embodiment Construction

[0016] figure 1 A diagram schematically shows an aircraft landing gear 100 according to one embodiment of the present invention. The aircraft landing gear 100 is retractable into a landing gear compartment (not shown) provided in the fuselage 10 of the aircraft. A retract / extend mechanism 104 is provided to move the landing gear 100 into and out of the landing gear bay.

[0017] The landing gear 100 includes a landing gear frame 102 pivotally mounted on a first end 114 within the landing gear bay. The landing gear 100 also includes a gear train unit 108 connected to a shock-absorbing oil damper (oleo) 112 and torsion link 106 . The hydraulic shock absorber 112 and the twisted link 106 are connected via the landing gear steering system 110 to a strut portion 116 disposed on a second end of the landing gear frame 102 remote from the first end 114 thereof.

[0018] The landing gear steering system 110 includes a harmonic drive coupled to the interior (for example, see figure...

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PUM

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Abstract

The invention relates generally to an aircraft landing gear steering system (110, 210, 310) comprising a turning member (118, 218, 318) that is operably coupled to a landing gear leg (116, 216, 316) through a harmonic drive mechanism (260, 360). The landing gear steering system 110 may be electrically driven. The system typically comprises a flex spline (239), for providing a low gear ratio. The system may also comprise a steering drive disengagement clutch. Additionally, the landing gear system (110, 210, 310) has various advantages, including the provision of a safe failure mode should the harmonic drive mechanism (260, 360) fail.

Description

technical field [0001] The present invention relates generally to aircraft landing gear. In particular, the present invention relates to an improved aircraft landing gear steering system. Background technique [0002] Most aircraft, especially those heavier than air, have some type of landing gear. Such landing gear often takes the form of one or more sets of freely rotatable wheels provided on individual wheel train units that can be independently retracted into individual landing gear bays within the fuselage of the aircraft, thereby Reduced induced drag in flight. Typically, one or more of the gear train units are also steerable so that the pilot can direct the aircraft on the ground. For example, it is very common to have a three-wheeled type landing gear arrangement in which the gear train units of the nose wheels can be independently rotated relative to the aircraft fuselage to steer the aircraft. [0003] Various steering arrangements for aircraft landing gear are...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/50
CPCB64C25/505B62D3/02B64C25/50F16H49/001Y10T74/19
Inventor R·汉弗莱
Owner TRIUMPH ACTUATION SYST UK
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