Control system fatigue test loading device

A technology of fatigue test and loading device, which is applied in the field of fatigue test to achieve the effect of protecting the test piece

Active Publication Date: 2021-04-06
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of this application is to provide a loading device for the fatigue test of the control system to solve at least one problem in the prior art

Method used

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  • Control system fatigue test loading device
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  • Control system fatigue test loading device

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Embodiment Construction

[0029] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the technical field of fatigue tests, and particularly relates to a control system fatigue test loading device. The device comprises an actuator, a fixing plate, a limiting screw rod, a pulling direction limiting plate, a pressing direction limiting plate and an actuating block. An outer cylinder base and an actuating rod are arranged on the actuator; the fixed plate sleeves the outer side of the actuating rod through the first through hole and is fixedly connected with one end of the outer cylinder base; the limiting screw rod is fixedly mounted in the first mounting hole of the fixed plate; the pull direction limiting plate sleeves the outer side of the actuating rod through the second through hole and is fixedly connected with the limiting screw rod through the second mounting hole; the pressing direction limiting plate sleeves the outer side of the actuating rod through a third through hole and is fixedly connected with the limiting screw rod through a third mounting hole, and a preset distance is formed between the pressing direction limiting plate and the pull direction limiting plate; and the actuating block is fixedly connected with the actuating rod through the fourth mounting hole, and is limited between the pull direction limiting plate and the pressing direction limiting plate. According to the invention, the moving position of the actuating rod can be actuated, thereby protecting the test piece.

Description

technical field [0001] The application belongs to the field of fatigue test technology, in particular to a loading device for fatigue test of a control system. Background technique [0002] The control system is the most critical system of a manned aircraft, which is related to the survival of the aircraft. In order to ensure the safe operation of the control system during the service period of the aircraft, the fatigue test of the control system is very important. [0003] Since the fatigue test of the control system is to simulate the pilot's control action during flight, the load is generally small, and the test piece is more likely to be damaged under the wrong load. The existing test loading protection method is mainly the pressure relief protection of the hydraulic sub-station, but because the pressure of the hydraulic sub-station is not directly unloaded to zero, the protection caused by the wrong signal fed back by the sensor failure during the test will cause impact...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00B64F5/60
CPCG01M13/00B64F5/60
Inventor 牛会杰郭小鹏栾胜坤
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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