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Aircraft nose landing gear steering system

A front landing gear, aircraft technology, applied in landing gear, aircraft parts, wheeled and other directions, can solve the problem of limited turning angle of the front wheel, unable to turn, etc., and achieve the effect of small turning radius, uniform force and stable structure

Active Publication Date: 2020-07-24
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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  • Aircraft nose landing gear steering system

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Embodiment Construction

[0038] Specific implementations of the present invention will be described below. It should be noted that in the specific description of these implementations, in order to make a 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 implementation mode, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer, in order to meet the system-related or business-related restrictions, A variety of specific decisions are often made, and this will change from one implementation to another. In addition, it is also understandable that although the efforts made in this development process may be complicated and lengthy, for those of ordinary skill in the art related to the content disclosed in the present invention, the technology disclosed in this disclosure Some design, ma...

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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 turning system of the nose gear of an aircraft. Background technique [0002] At present, the turning system of civil aircraft generally uses actuators to complete the rotation of the front wheels. At present, the core component of the front wheel turning system is a push-pull actuator or a rack and pinion actuator. The turning principle is: through the actuator, the front wheel rotates at a certain angle around the axial direction of the front landing gear pillar 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 be turned at any angle. Summary of the invention [0004] An object of the present invention is to overcome the defects of the existing aircraft nose gear turning system and provide a new aircraft nose gear turning system, which can enable the aircraft to have an arbitrary turning angle and a smaller turning radius. [0005] The abov...

Claims

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Application Information

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Patent Type & Authority Patents(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