Multi-working-condition simulated aircraft wire harness abrasion experiment equipment and experiment method

A technology of experimental equipment and experimental methods, which is applied in the field of aircraft harness wear test equipment for multi-working condition simulation, can solve problems such as narrow cabin space, reduced service life of wire harness, signal transmission quality, wear and tear between aircraft wire harness and structure, and achieve stable movement , the effect of easy installation

Active Publication Date: 2020-12-04
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Compared with large military / civilian aircraft, due to the limitation of the body structure of the fighter jet, the cabin space is narrow, and when the wiring harness is laid and installed, it may interfere with the structure at the frame passing and insufficient clearance, or the maximum package of the wiring harness shakes due to the high-frequency vibration of the aircraft. If the gap between the fuse body and the aircraft structural parts is less than or equal to zero, it will cause direct wear between the aircraft wiring harness and the structure, reducing the service life of the wiring harness and the transmission quality of the signal
In the existing technology, the research on the wear of aircraft wiring harness is still immature, and it is necessary to better study the reasonable anti-wear process of the wiring harness, including the performance of the wear-resistant material of the wiring harness and the installation clearance of the wiring harness, etc.

Method used

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  • Multi-working-condition simulated aircraft wire harness abrasion experiment equipment and experiment method
  • Multi-working-condition simulated aircraft wire harness abrasion experiment equipment and experiment method
  • Multi-working-condition simulated aircraft wire harness abrasion experiment equipment and experiment method

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Experimental program
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Effect test

Embodiment 1

[0045] As a basic embodiment of the present invention, the present invention includes a multi-working-condition simulation aircraft harness wear test equipment, including a test bench 1, a signal acquisition device, two clamping devices 2 and an excitation device. The clamping device 2 is hinged with a vertical plate 14 , and the vertical plate 14 is connected with a fixing piece for fixing the aircraft wire harness or the wire harness wear test object, and the fixing piece can be a wire harness clamp 12 . The wire harness wear test object may be a wire harness, and the aircraft wire harness and the two ends of the wire harness are respectively fixed on the vertical plate 14 through the wire harness clamp 12 . The aircraft wire harness and the wire harness are simultaneously fixed by the two clamping devices 2 , and the distance between the aircraft wire harness and the wire harness can be adjusted by adjusting the wire harness clip 12 .

[0046] The vibration excitation devic...

Embodiment 2

[0049] As a preferred embodiment of the present invention, the present invention includes a multi-working-condition simulation aircraft harness wear test equipment, including a test bench 1, a signal acquisition device, three clamping devices 2 and two vibration excitation devices. Two of the clamping devices 2 are hinged with a vertical plate 14, and the vertical plate 14 is connected with a wire harness clamp 12 for fixing the aircraft wiring harness, so that the two clamping devices 2 are respectively located at two ends of the aircraft wiring harness. The vertical plate 14 on the other clamping device 2 is connected with a test piece chuck 5 for fixing the test object of wire harness abrasion. The aircraft wire harness and the wire harness wear test object are fixed separately to facilitate the adjustment of the distance between them.

[0050] The test bench 1 is provided with a number of evenly spaced chutes, and the lower surface of the clamping device 2 and the mounting...

Embodiment 3

[0054] As the best implementation mode of the present invention, with reference to the attached figure 1 , The present invention includes a multi-working condition simulation aircraft harness wear test equipment, including a test bench 1, a signal acquisition device, four clamping devices 2 and two excitation devices. The test bench 1 is provided with a plurality of sliders 6 , and the sliders 6 are evenly arranged along the length direction of the test bench 1 , and the sliders 6 run through the width direction of the test bench 1 .

[0055] The clamping device 2 includes an installation base plate 13 and a vertical plate 14 hinged on the installation base plate 13, and four base plate installation holes for matching with bolts are provided around the installation base plate 13. The vertical plates 14 on the two clamping devices 2 are connected with a fixing part for fixing the aircraft wiring harness, which can be a wire harness clamp 12; the vertical plates 14 on the other ...

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PUM

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Abstract

The invention relates to the technical field of aircraft wire harness experiments, in particular to multi-working-condition simulated aircraft wire harness abrasion experiment equipment and an experiment method. The multi-working-condition simulated aircraft wire harness abrasion experiment equipment comprises an experiment table, a signal acquisition device, at least two clamping devices and at least one excitation device; the installation distance between an aircraft wire harness and a wire harness abrasion experiment object can be preset; and a vibration exciter is used for loading a vibration environment to directly excite the aircraft wire harness, so that the aircraft wire harness mounting area achieves a vibration state meeting the working condition requirements, and the aircraft wire harness anti-abrasion process research is carried out. Through the experiment equipment and the experiment method, the state of the aircraft wire harness can be monitored in real time, the stress condition of the aircraft wire harness under different working conditions is collected, and data support is provided for an aircraft wire harness anti-abrasion process.

Description

technical field [0001] The invention relates to the technical field of aircraft wire harness experiments, in particular to an aircraft wire harness wear test equipment and an experiment method for multi-working condition simulation. Background technique [0002] Modern advanced fly-by-wire aircraft use wiring harness as a medium to connect the airborne equipment scattered in each cabin of the aircraft to transmit information and energy. As the neural network of the aircraft system, the wiring harness directly affects the reliability of the overall function and performance of the aircraft, and even adversely affects the safety of the aircraft. In civil / military aircraft electrical wiring interconnection systems, effective means are required to prevent harmful wear between harness and harness, harness and structure, or harness and equipment. The quality of harness assembly is especially important. [0003] Compared with large military / civilian aircraft, due to the limitation...

Claims

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Application Information

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IPC IPC(8): G01N3/56
CPCG01N3/56G01N2203/0005G01N2203/028G01N2203/04G01N2203/005
Inventor 王丹阳张永建谢银唐健钧丁晓叶波刘禹宏
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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