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Aircraft landing gear test loading device and testing method

A technology of aircraft landing gear and loading device, which is applied in the direction of aircraft component testing, weight reduction, etc., can solve the problems of inability to load at both ends of the axle, and achieve good interchangeability, convenient installation, and light weight

Active Publication Date: 2020-11-24
XIAN AIRCRAFT IND GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the current integrated loading device determines that it cannot independently load the two ends of the axle from the structural form.

Method used

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  • Aircraft landing gear test loading device and testing method
  • Aircraft landing gear test loading device and testing method
  • Aircraft landing gear test loading device and testing method

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Embodiment Construction

[0013] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention.

[0014] Such as figure 1 As shown, the loading device of the present invention mainly includes a rigid pillar 1 , a loading rocker arm 2 , a lateral loading lug 3 , and a reverse course loading lug 4 . The upper end of the rigid pillar 1 is a fork lug structure, the fork lug is provided with a coaxial connection hole, the loading rocker arm 2 is a cantilever structure, and the loading rocker arm body is provided with a central through hole connected with the fork lug. Three directions of loading cantilevers protrude from the rocker body, the middle direction is the vertical loading cantilever 8, the loading cantilevers on the left and right sides are symmetrical, one side is the course l...

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Abstract

The invention provides an aircraft landing gear test loading device and a testing method. The loading device comprises a rigid support column, a loading rocker arm, a lateral loading ear flake and a reverse course loading support lug, an aircraft landing gear is reversely fixed to a testbed, one loading device is fixed to each of two ends of a landing gear axle, a vertical actuating cylinder on the testbed is connected with a vertical loading cantilever of the loading rocker arm, a course dragging actuating cylinder is connected with a course loading cantilever of the loading rocker arm, a reverse course dragging actuating cylinder is connected with a reverse course loading cantilever of the loading rocker arm, a reverse course brake actuating cylinder is connected with the reverse courseloading support lug, a lateral actuating cylinder is connected with the lateral loading ear flake, and the lateral actuating cylinder applies landing gear lateral load to the loading device. The loading device can realize application of independent load to two ends of the axle, simulate the loading condition of the landing gear axle during actual using more accurately and improve reliability of atesting result effectively.

Description

technical field [0001] The invention relates to the field of aircraft landing gear strength test design, and specifically discloses an aircraft landing gear test loading device and a test method. Background technique [0002] Landing gear is a special device that provides an aircraft for takeoff, landing, taxiing and parking. Due to its single force transmission route, severe stress conditions, low probability of crack detection, and high crack growth rate, it is a key load-bearing component for safe take-off and landing of aircraft. Therefore, the strength test of landing gear occupies a very important position in aircraft design. The loading device that can accurately apply the load of the landing gear is the premise to improve the reliability of the test results. [0003] During the take-off, landing and ground handling of the aircraft, the landing gear bears vertical loads and acts on the axle position; it bears the traction load of the heading and reverse heading and ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60Y02T50/40
Inventor 陈奇薛长宝刘伟
Owner XIAN AIRCRAFT IND GROUP