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Fatigue load flexible applying system for aircraft vibration superposition fatigue strength test

A fatigue strength, fatigue load technology, applied in the field of fatigue load flexible application system, can solve the problems of high test cost, difficult implementation, complex technology, etc., to improve reliability and comprehensiveness, improve accuracy and comprehensiveness, structure Well-designed effects

Active Publication Date: 2022-07-22
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the existing follow-up loading system needs to develop the control algorithm and adjustment parameters separately, the technology is complex, the test cost is high, and the difficulty of implementation increases with the increase of the fatigue loading point

Method used

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  • Fatigue load flexible applying system for aircraft vibration superposition fatigue strength test
  • Fatigue load flexible applying system for aircraft vibration superposition fatigue strength test
  • Fatigue load flexible applying system for aircraft vibration superposition fatigue strength test

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] like figure 1 , 2 The fatigue load flexible application system for aircraft vibration superimposed fatigue strength test shown in , 6 includes test bench 1, support assembly 2 and connection assembly 3; The longitudinal section is an inverted U-shaped structure, six outer loading seats 40 are horizontally distributed on the outer wall of the test piece 4, and six inner loading seats 41 are horizontally divided on the inner wall of the test piece 4 away from the outer loading seat 40;

[0039] like figure 1 , 2 , 3 and 6, the support assembly 2 includes an inner fixing beam 20, an outer fixing beam 21, a loading rod 22, a loading fixing beam 23 and a steering fixing beam 24; the inner fixing beam 20, the outer fixing beam 21, the loading rod 22, the loading The fixed beam 23 and the steering fixed beam 24 are parallel to each other, the inner fixed beam 20 is arranged inside the test piece 4 and is fixedly connected with the upper end surface of the test bench 1, and ...

Embodiment 2

[0042] This embodiment differs from Embodiment 1 in that:

[0043] like figure 1 , 8 , 9, both ends of each connecting rubber rope 51 are provided with a quick connector 54, the quick connector 54 includes an outer casing 540, a clamping arc plate 541 and a fastening ring 542, the outer casing 540 is provided with two, two outer casings The bodies 540 are movably connected by threaded sleeves 543, the two outer shells 540 are provided with docking holes 544 on the side away from each other, and eight clamping arc plates 541 are provided, and each clamping arc plate 541 is articulated at two Inside the outer casing 540 and located in the circumferential direction of the docking hole 544 , there are two fastening rings 542 . The tapered holes 5420 are sleeved on the outside of each clamping arc plate 541 on the corresponding side, and a compression spring 545 is provided between the two fastening rings 542 and the inner bottom of the outer casing 540; each clamping arc plate 5...

Embodiment 3

[0045] This embodiment differs from Embodiment 1 in that:

[0046] like image 3 , 4 , 5, the fifth loading cable 34, the seventh loading cable 36 and the loading rod 22 are connected with a connecting seat 37, the connecting seat 37 includes a fixed seat 370 and a sliding sleeve 371, the fixed seat 370 and the loading rod 22 Fixed connection, the fixed seat 370 is provided with a wire cable slot 3700 inside, the sliding sleeve 371 is movably sleeved outside the fixed seat 370, and the inside of the sliding sleeve 371 is provided with a clip 3710 corresponding to the position of the wire cable slot 3700, on the sliding sleeve 371 A tightening screw 372 threadedly connected to the fixing seat 370 is provided through; the inner wall of the sliding sleeve 371 is provided with a guide block 3711 , and the outer wall of the fixing seat 370 is provided with a guide chute 3701 slidably engaged with the guide block 3711 .

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PUM

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Abstract

The invention discloses a fatigue load flexible applying system for an aircraft vibration superposition fatigue strength test, and belongs to the technical field of aircraft testing, and the applying system comprises a test bench, a supporting assembly and a connecting assembly; a test piece is arranged on the test bed, the supporting assembly comprises an inner side fixing beam, an outer side fixing beam, a loading rod, a loading fixing beam and a steering fixing beam, the inner side fixing beam, the outer side fixing beam, the loading fixing beam and the steering fixing beam are connected with the inner wall of the test room, and the loading rod is located between the outer side fixing beam and the loading fixing beam. The connecting assembly is used for connecting the inner side fixing beam, the outer side fixing beam, the loading rod, the loading fixing beam, the steering fixing beam and the test piece; the application system is reasonable in structural design, and the accuracy of an airplane vibration superposition fatigue strength test result can be improved.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to a fatigue load flexible application system used for aircraft vibration superimposed fatigue strength testing. Background technique [0002] The vibration superimposed fatigue strength test refers to a type of aircraft test test in which there are both vibration loads and fatigue loads in the test load; it is aimed at the structural parts of the helicopter's main bearing structure that are subjected to severe vibration loads and fatigue loads at the same time during use. , simple vibration test or fatigue test cannot simulate its environmental load, so carrying out vibration superimposed fatigue strength test can study the dynamic characteristics and damage accumulation process of the structure under the premise of simulating its environmental load as much as possible. It is of great significance to guide the optimal design of aircraft structure. [0003] Applying load i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M7/02B64F5/60G01M99/00G01N3/34G01N3/14G01N3/02
CPCG01M7/02G01M99/005G01M99/007B64F5/60G01N3/34G01N3/14G01N3/02G01N2203/0003G01N2203/0005G01N2203/0033G01N2203/0032G01N2203/0073Y02T90/00
Inventor 王彬文刘海涵黄文超潘凯王纯
Owner CHINA AIRPLANT STRENGTH RES INST
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