Undercarriage ejection main force transmission structure fatigue test device and test method thereof

A fatigue test and landing gear technology, which is used in the testing of machine/structural components, measuring devices, and aircraft component testing. Simple installation and good continuity

Active Publication Date: 2020-05-05
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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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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  • Undercarriage ejection main force transmission structure fatigue test device and test method thereof
  • Undercarriage ejection main force transmission structure fatigue test device and test method thereof
  • Undercarriage ejection main force transmission structure fatigue test device and test method thereof

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Embodiment Construction

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

[0029] like 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 opposite vertical beams 5, and an upper beam 7 and a lower beam 8 are respectively arranged along the 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] like 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 the device to e...

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Abstract

The invention provides an undercarriage ejection process main force transmission structure fatigue test device and test method. The device comprises an ejection rod, a rotating sleeve, an upper torsion arm, a lower torsion arm, an ejection load loading mechanism, a traction load loading mechanism and a main force transmission device fixing mechanism. The test method mainly comprises steps of (1) mounting and fixing a test piece, (2) mounting and fixing an ejection loading device mechanism, (3) installing and fixing the traction loading device mechanism, (4) performing cyclic loading test, and(5) testing the residual strength under the working condition of the maximum catapulting force. The device is advantaged in that the fatigue life of a main force transmission structure is measured, ahydraulic actuating cylinder is adopted for loading, so the load is stable, and continuity is good; arrangement and installation of the test device can accurately simulate the real working condition of the main force transmission structure, construction and installation are simple, a test scale is reduced, and test cost is saved.

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 Applications(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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