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Aircraft landing gear landing drop test system

A technology of aircraft landing gear and test system, applied in the direction of aircraft component testing, etc., can solve the problem that the test equipment cannot support the efficient experimental process, etc., and achieve the effect of improving safety performance and comfort performance, high experimental value, and comprehensive considerations.

Inactive Publication Date: 2021-02-02
廖彩龙
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Most of the test equipment in service is difficult to support efficient experimental process

Method used

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  • Aircraft landing gear landing drop test system
  • Aircraft landing gear landing drop test system
  • Aircraft landing gear landing drop test system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0045] When testing, the operator should first take out the corresponding counterweight 13, place a certain specification of counterweight 13 on the No. 3 fixing plate 21 to fix it, and adjust the angle between the No. The distance between 10 and 10, and then adjust the different landing angles when the aircraft lands, and then fix the take-off tester 9 on the jack 1, and use the jack 1 to lift the take-off tester 9 to the ejection platform 16 to ensure the take-off test. The pulley 15 on the instrument 9 is embedded in the slide rail 5 and can slide relative to the slide rail 5 to adjust the elastic force and direction of the No. 1 spring column 18. The ejection plate 19 plays a role in ejecting the lift tester 9. By changing the No. 1 spring column 18, so that the landing tester 9 can obtain the required different initial speeds, the pulley 15 slides on the slide rail 5 through the acceleration of the catapult 3 and reaches the highest point of the slide rail 5, and then the ...

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PUM

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Abstract

The invention discloses an aircraft landing gear landing drop test system, which comprises a jack, an ejection table upright post, an ejector, a supporting column, a slide rail, a connecting rail, a horizontal beam, a plurality of vibration measuring instruments and a landing test instrument, and is characterized in that the ejector is fixed on the upper surface of the ejection table upright post,and the jack is positioned below the right side of the ejector; the slide rail is fixed to the upper surface of the supporting column, the two ends of the connecting rail are connected with the sliderail and the horizontal beam respectively, the horizontal beam is connected with the jack, the vibration measuring instruments are fixed to the lower portion of the supporting column and embedded inthe middle of the horizontal beam, and the landing test instrument is hung on the horizontal beam. The landing angle of the landing test instrument can be adjusted, the landing test instrument can bematched with the slide rail to achieve multi-angle landing, later experiment comprehensiveness is facilitated, and the angle most suitable for landing of an undercarriage can be found through experiments.

Description

technical field [0001] The invention relates to an aircraft landing gear landing shock test system, in particular to an aircraft landing gear landing shock test system, which belongs to the application field of aircraft landing gear landing shock tests. Background technique [0002] With the continuous improvement of my country's economic level and better living standards, people's demand and comfort for daily travel are also increasing, and the safety and comfort of aircraft landing has become an issue that people are increasingly concerned about. An aircraft landing system with high safety and high comfort is undoubtedly a milestone in the advancement of technology and even life. However, because the safe landing of the aircraft landing gear involves many complex factors, it is a difficult and even more important point to study its all-round process. [0003] Most of the existing test equipment is difficult to support efficient experimental process. The aircraft landing ...

Claims

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Application Information

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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 不公告发明人
Owner 廖彩龙
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