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Fatigue test device and test method for main force transmission structure of landing gear ejection

A fatigue test and landing gear technology, which is applied in the testing of machine/structural components, measuring devices, aircraft component testing, etc., can solve the problems of no fatigue test, no relevant research, and less public content, and achieve simple and continuous construction and installation Good performance and reduced test size

Active Publication Date: 2021-09-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, there is no relevant public test research report on the fatigue test of the landing gear restraining ejection force transmission structure in China, and foreign research on this aspect started earlier, but the public content is very little
And there is no relevant research in the currently published patents
Most of the relevant literature is the theoretical analysis of the landing gear ejection process, the software simulation research of the landing gear ejection take-off dynamics, the optimization of the landing gear ejection take-off parameters, etc., and there is no relevant fatigue test research

Method used

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  • Fatigue test device and test method for main force transmission structure of landing gear ejection
  • Fatigue test device and test method for main force transmission structure of landing gear ejection
  • Fatigue test device and test method for main force transmission structure of landing gear ejection

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Embodiment Construction

[0028] The present invention will be further explained below in conjunction with the accompanying drawings.

[0029] Such as figure 1 The fatigue test device for the main force transmission structure during the ejection process of the landing gear is shown, including the ejection rod 1, the rotating sleeve 2, the upper torque arm 3, the lower torque arm 4, the ejection load loading mechanism, the pinning load loading mechanism and the main force transmission mechanism. Device fixing mechanism. It also includes two vertical beams 5 arranged oppositely, and an upper beam 7 and a lower beam 8 are respectively arranged along a direction perpendicular to the vertical beams 5 . The top of the vertical beam 5 is also provided with a top beam 6 for fixing.

[0030] Such as figure 2 As shown, the vertical beam structure is supported by fixed brackets 13 . The fixed support 13 is a triangular support, which is provided with 2 groups, which are respectively arranged on both sides of...

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Abstract

The invention provides a fatigue test device and test method for the main force transmission structure during the ejection process of the landing gear. The force device fixing mechanism; the test method mainly includes the following steps: (1) installation and fixing of the test piece; (2) installation and fixing of the ejection loading device mechanism; (3) installation and fixing of the restraining loading device mechanism; (4) cyclic loading test; (5) Residual strength test for the maximum ejection force condition. The invention measures the fatigue life of the main force transmission structure; adopts the hydraulic cylinder to load, the load is stable and the continuity is good; the layout and installation of the test device can accurately simulate the real working conditions of the main force transmission structure, and at the same time, the construction and installation are simple, reducing the The test scale saves test cost.

Description

technical field [0001] The invention relates to the technical field of fatigue test of the main force transmission structure of the landing gear ejection, in particular to a fatigue test device and the test method of the main force transmission structure of the landing gear ejection. Background technique [0002] There are three ways for carrier-based aircraft to take off on the aircraft carrier: autonomous take-off, ski jump take-off, and catapult take-off, among which catapult take-off is divided into steam catapult and electromagnetic catapult. The catapult take-off has the advantages of high efficiency, short ejection period, simple ejection, and does not distinguish the type of landing gear. It can give full play to the combat performance of the landing gear and the aircraft carrier, which is an inevitable direction of future development. [0003] When the aircraft is ejected and taken off, the drag shuttle on the catapult is connected to the ejection bar of the front l...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60G01M13/00
CPCB64F5/60G01M13/00
Inventor 聂宏陈虎魏小辉房兴波张钊王添翼
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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