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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AI-Extracted 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 wil...

Method used

1. local grinding is carried out to sticking strain gauge 3 positions and make surface roughening to strengthen pasting effect, adopt circle formula grinding during grinding, then clean with acetone and alcohol, to remove greasy dirt, until the absorbent cotton for cleaning is no longer discolored until;

[0049] As a preferred embodiment of the present invention, the present invention includes a multi-mode simulated aircraft harness wear test equipment, including a test bench 1, a signal acquisition device, three clamping devices 2 and two 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 re...

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.

Application Domain

Investigating abrasion/wear resistance

Technology Topic

AirplaneMechanical engineering +3

Image

Examples

Experimental program(3)
Effect test(1)

Example Embodiment

[0044] Example 1

[0045] Embodiment of the present invention as a basic embodiment, the present invention comprises a wear test apparatus for an aircraft harness multi-condition simulation, including a signal acquisition means, two clamping means 2 and a bench excitation device. The holding means 2 is hinged on the vertical plate 14 connected to the fixing member for fixing an aircraft harnesses or harness worn on the subject's vertical plate 14, the fixing member may be a wire harness clamp 12. Subjects wear the wire harness may be a wiring harness, the harness and harness aircraft ends respectively fixed to a wire harness clamp 1412 on the riser. 2 while fixing plane by the wire harness and a wire harness two holding means 12, the aircraft can adjust the spacing between the harness and the harness by the harness clamp adjusting.

[0046] Said excitation means comprises a mounting plate and electrically connected sequentially exciter 4, a power amplifier and a signal generator 9. The bench is provided with a plurality of uniformly disposed slider 6, the clamping device 2 and the lower surface of the mounting plate 6 is provided with a slider chute 15 matches 1, the holding means 2 and the mounting plate 1 in conjunction with test bed are slidably connected through the chute 15 and the slider 6. The mounting plate is also provided with a through hole, the through hole provided with a circular slide, wherein the outer wall is provided with an annular circular sliders slide, the inner wall of the through hole of the slider is provided with an annular groove that matches the annular circular slide plate can be rotated relative to the mounting. The exciter sliding table 4 is fixed in the circular surface, so that the exciter 4 can rotate with respect to the mounting plate.

[0047] Using an excitation force exciter 4 and provide an adjustable frequency power to the aircraft wire harness, the wire harness direct excitation of the aircraft, the aircraft being mounted such that the harness vibration region obtained state satisfies the conditions required, according to specific working conditions, so that jack exciter vibration applied to the wire harness 4 in the horizontal direction or vertical direction. The signal acquisition device 3 comprises a strain gauge, an information processor PC 7 and 8, the information processor 8 comprises a signal conditioner electrically connected sequentially, the AD converter and a digital signal processor, the information processor through 8 a communication cable 10 is connected to the signal generator 9, connected by a signal cable 11 and the acquisition of the strain gage signal conditioner 3.

Example Embodiment

[0048] Example 2

[0049] As a preferred embodiment of the present invention, the present invention is an aircraft comprising a multi-wire harness wear test condition simulation device comprising a signal acquisition device, the clamping device 2 and the three excitation device two bench. 2 wherein the holding means has two hinged vertical plate 14 is connected to a wire harness clamp for fixing the wire harness 14 of the aircraft vertical plate 12, so that the two clamping means 2 at each end of the aircraft wire harness. Test pieces 5 connected to the chuck for fixing a harness 14 worn on the subject's upright plate 2 on the other holding means. Aircraft harnesses and harness are fixed subjects wear, easy to adjust the spacing therebetween.

[0050] The test station has a plurality of evenly spaced on the chute 1, the lower surface of the gripping means 2 and the mounting plate are provided with two slide chutes match, wherein the distance between the two sliders to match the spacing between two adjacent chute. Sliding along the longitudinal direction of the bench 1 is uniformly disposed, and through the chute 1 in the width direction of the bench. The gripping means 2 and the mounting plate in conjunction with test bed through a chute connected to the slide of the slider.

[0051] Said excitation means comprises a mounting plate and electrically connected sequentially exciter 4, a power amplifier and a signal generator 9. The exciter 4 is positioned on the mounting plate, capable of rotation relative to the mounting plate. The aircraft also has a harness clamp member, said exciter jack 4 are connected to the threaded collar portion. Vibration is applied to a horizontal plane of the wire harness, a further vibration is applied in the vertical direction of the aircraft wire harness.

[0052] The signal acquisition device 3 comprises a strain gauge, an information processor PC 7 and 8, the information processor 8 comprises a signal conditioner electrically connected sequentially, the AD converter and a digital signal processor, the information processor through 8 a communication cable 10 is connected to the signal generator 9, connected by a signal cable 11 and the acquisition of the strain gage signal conditioner 3.

Example Embodiment

[0053] Example 3

[0054] As a preferred embodiment of the present invention, with reference to the specification attached figure 1 The present invention is an aircraft comprising a multi-wire harness wear test condition simulation device comprising a bench, a signal acquisition device, four clamp device 2, and two excitation device. The test bed 1 is provided with a plurality of slide 6, the slide 6 along the longitudinal direction of the test station 1 is uniformly arranged, and the width direction of the slider 6 through a test station.

[0055] The clamp 2 and the hinge comprises a mounting plate 13 mounted on the vertical plate 13 of the bottom plate 14, mounting board 13 is also provided with four weeks for four floor mounting holes match with the bolt means. Wherein the connector on the upright plate 2 clamping means 14 is provided with two fixing members for fixing the aircraft wire harness, the fixing member may be a wire harness clamp 12; 14 connected to the upright plate 2, two additional clamping means for fixing fixing the wire harness wear test object, fixing the test piece member may be a chuck 5, wherein the wire harness may be worn subjects or harness frame structure, piping and other equipment for the aircraft structure or on the aircraft.

[0056] Said excitation means comprises a mounting plate, and a condition analysis system signal generating system, wherein the operating condition analyzing system comprises the harness condition analysis, vibration required, the voltage phase of the output frequency of three parts. The signal generating system includes a signal generator 9, the power amplifier 4 and exciter. The exciter mounting plate 4 is located, capable of rotating relative to the mounting plate, the mounting plate may be specifically provided with a rotating member, the rotating member is located on the exciter 4, rotated by the rotation of the exciter member 4 to achieve rotation, to achieve adjustable angle position. The aircraft also has a harness clamp member, said exciter jack screw and clamp member 4 are connected. With this structure, vibration is applied to achieve horizontal plane of a wire harness jack exciter 4, further applied to the vibration exciter of the jack 4 in the vertical direction of the aircraft wire harness.

[0057] The lower surface of the mounting board holding means 2 and the mounting plate 13 are provided with excitation means 6 matches with the slider chute 15, wherein each of the sliding structure has a configuration of the four through- groove 15, and the four chutes 15 disposed crosswise of formula, with the same pitch direction between the two chutes 15, and the spacing between the adjacent two of the slider 6 matches. Such that the gripping means 2 and the mounting plate are connected by a sliding fit with the experimental stage chute 15 and the slider 6 1.

[0058] The signal acquisition device 3 comprises a strain gauge, and the host computer 8 information processor 7, the strain gauge 3 is connected through a signal cable 11 and the information acquisition processor 8, the information processor comprises a signal conditioning 8 are sequentially electrically connected is, the AD converter and a digital signal conditioner 10 through the communication cable 9 is connected to an information processor and the signal generator 8.

PUM

Description & Claims & Application Information

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Classification and recommendation of technical efficacy words

mobile stability
Easy to install

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

AI-Extracted Technical Summary

Problems solved by technology

Method used

Abstract

Image

Examples

Example Embodiment

Example Embodiment

Example Embodiment

PUM

Description & Claims & Application Information

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