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An aircraft landing gear test loading device and test 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 that the two ends of the axle cannot be loaded, and achieve the effects of good interchangeability, small size, and convenient installation

Active Publication Date: 2022-07-12
XIAN AIRCRAFT IND GROUP
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  • Description
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  • 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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  • An aircraft landing gear test loading device and test method
  • An aircraft landing gear test loading device and test method
  • An aircraft landing gear test loading device and test 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 with reference to the accompanying drawings in the embodiments of the present invention.

[0014] like figure 1 As shown, the loading device of the present invention mainly includes a rigid strut 1 , a loading rocker arm 2 , a side loading lug 3 , and a reverse course loading lug 4 . The upper end of the rigid strut 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 to the fork lug. Loading cantilevers in three directions protrude from the rocker body, the middle direction is the vertical loading cantilever 8, the left and right sides of the loading cantilever are symmetrical, one side is the heading ...

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Abstract

An aircraft landing gear test loading device and a test method, the loading device comprises a rigid strut, a loading rocker arm, a side loading lug and a reverse course loading lug, the aircraft landing gear is fixed upside down on a test bench, and the landing gear axle A loading device is fixed at both ends of the test bench to connect the vertical actuating cylinder on the test bench with the vertical loading cantilever of the loading rocker arm, connect the directional traction actuating cylinder to the directional loading cantilever of the loading rocker arm, and connect the reverse heading The traction actuator is connected to the reverse course loading cantilever of the loading rocker, the reverse course brake actuator is connected to the reverse course loading lug, the side actuator is connected to the side loading lug, and the side actuator is connected to the side loading lug. Apply side load on the landing gear to the loading device. The loading device can satisfy independent loads on both ends of the wheel axle, more accurately simulate the loading situation of the wheel axle of the landing gear in actual use, and effectively improve the reliability of the test results.

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 aircraft for take-off, landing, rollout and parking. Because of its single force transmission route, serious force situation, low crack detection probability and high crack propagation rate, it is a key load-bearing component for safe take-off and landing of aircraft. Therefore, the strength test of the landing gear occupies a very important position in the aircraft design. The loading device that can accurately apply the landing gear load is the premise to improve the reliability of the test results. [0003] During the take-off, landing and ground control of the aircraft, the landing gear is subjected to vertical loads and acts on the wheel axle; it is subjected to the traction load of the heading and r...

Claims

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Application Information

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