Airplane front landing gear outer cylinder support rod connector traction takeoff static force testing method

Abstract

The invention provides an airplane front landing gear outer cylinder support rod connector traction takeoff static force testing method which comprises the following steps: according to a bearing situation of an outer cylinder support rod connector, confirming a key stress part and a strain piece pasting position of the outer cylinder support rod connector; detecting a strain piece, and ensuring that the survival rate of the strain is 95% or greater in loading measurement; manufacturing a sample part of the outer cylinder support rod connector, mounting the sample part on a clamp, and exertinga load; implementing loading testing, including pre-testing and official testing, exerting a limit load of 60% from a limit load of 5% step by step in pre-testing, implementing 100% limit load testing once and implementing 150% extreme load testing once in official testing, exerting loads according to the 5% limit load step by step in the 100% limit load testing, exerting loads for the former 100% limit loads according to 5% limit loads step by step and exerting loads for the later 50% limit loads according to 2% limit loads step by step in the 150% extreme load testing, and judging that theouter cylinder support rod connector is qualified in the static force testing if the sample part is not damaged in the testing. By adopting the static force testing method provided by the invention, the fatigue properties and the service lives of partial structures are verified in advance by testing test parts, and the research cost is reduced.

Description

Technical field [0001] The invention belongs to the field of aircraft structure design, in particular to the field of aircraft structure testing, in particular to a static test method for traction and take-off of an aircraft's front landing gear outer cylinder support rod joint. Background technique [0002] In order to ensure the carrying capacity and life requirements of the nose landing gear of the aircraft used for towing and takeoff in the marine environment, the structural form and carrying capacity of the nose landing gear are obviously strengthened. The nose landing gear needs to bear a large towing load, and the vertical load is about that of an ordinary aircraft. More than 2 times of the gear, and the landing gear strut joints need to bear the full traction load. As a newly designed landing gear, if the full-scale landing gear is directly used for static test, there are disadvantages such as long production and manufacturing cycle of test pieces, long test bench design ...

AI Technical Summary

Problems solved by technology

As a newly designed landing gear, if the full-size landing gear is directly used for static tests, there are shortcomings such as long production and manufacturing cycles of test pieces, long test bench design and manufacturing cycles, long test cycles, and high development costs, and the test does not pass subsequent changes. longer period

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