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Turning system of airplane front landing gear

A front landing gear and aircraft technology, applied in landing gear, aircraft parts, transportation and packaging, etc., can solve the problems of inability to turn and the limited turning angle of the front wheel, and achieve uniform force, small turning radius, and shortened taxiing time. Effect

Active Publication Date: 2018-02-27
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The disadvantages of the prior art are: the front wheel has a limited turning angle and cannot turn at any angle

Method used

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  • Turning system of airplane front landing gear

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Embodiment Construction

[0038] Specific implementations of the present invention will be described below. It should be noted that in the process of specific descriptions of these implementations, for the sake of concise description, it is impossible for this specification to describe all the features of the actual implementations in detail. It should be understood that, in the actual implementation process of any embodiment, just like in the process of any engineering project or design project, in order to achieve the developer's specific goals and to meet system-related or business-related constraints, Often a variety of specific decisions are made, and this can vary from one implementation to another. In addition, it will be appreciated that while such development efforts may be complex and lengthy, the technology disclosed in this disclosure will be Some design, manufacturing or production changes based on the content are just conventional technical means, and should not be interpreted as insuffic...

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PUM

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Abstract

The invention relates to a turning system of an airplane front landing gear. The turning system of the airplane front landing gear comprises a front landing gear support column, a spherical hood, a spherical wheel and a bearing ball, wherein the spherical hood is detachably installed at the lower part of the front landing gear support column so as to accommodate the spherical wheel, the lower partof the spherical hood is designed in a tightening manner so as to prevent the spherical wheel from falling off, the bottom of the front landing gear support column is provided with a groove, the bearing ball is accommodated in the groove, and the bearing ball is connected between the front landing gear support column and the spherical wheel. The turning system of the airplane front landing gear has the following beneficial effects of enabling an airplane to turn at any angle and realizing smaller turning radius.

Description

technical field [0001] The invention relates to a steering system of an aircraft nose landing gear. Background technique [0002] At present, the turning system of civil aircraft is generally completed by using actuators to turn the front wheels. The core component of the current front wheel steering system is a push-pull actuator or a rack and pinion actuator. The turning principle is as follows: through the actuator, the front wheel is turned around the axial direction of the front landing gear strut by a certain angle to realize the front wheel turning. [0003] The disadvantage of the prior art is that the front wheel has a limited turning angle and cannot turn at any angle. Contents of the invention [0004] An object of the present invention is to overcome the defects of the existing aircraft nose landing gear turning system, and provide a new aircraft nose landing gear turning system, which can make the aircraft have any turning angle and smaller turning radius. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/36B64C25/50
CPCB64C25/36B64C25/50
Inventor 李冰肖扬姜逸民陆波曹丹青
Owner COMAC