Aircraft front undercarriage outer cylinder bracing joint traction take-off fatigue test method

Abstract

The invention provides an aircraft front undercarriage outer cylinder bracing joint traction take-off fatigue test method which comprises the following steps that an outer cylinder bracing joint testsample piece is subjected to a static strength test; a fatigue test is conducted, loads in X,Y and Z directions are harmoniously applied, a sinusoidal wave cyclic loading mode with the stress ratio of0.06 is adopted, and the loading frequency is 2 Hz; and the fatigue test is conducted in two stages, specifically, as for the first stage, the cyclic number of times of load applying is 7500, a visual test is conducted every 500 times, if the fatigue damage phenomenon occurs, the test is stopped, parameters are recorded, if not, the test piece is subjected to damage detection, and after the testpiece is qualified, the fatigue test enters into the second stage; and as for the second stage, the cyclic number of times of load increasing is 7500-15000, the visual test is conducted every 500 times, if the fatigue damage phenomenon occurs, the test is stopped, parameters are recorded, if not, the test is continued till the end, and the cyclic number of times is recorded. According to the aircraft front undercarriage outer cylinder bracing joint traction take-off fatigue test method, by testing the test piece, the fatigue property and the life of a local structure are verified in advance, and the development cost is reduced accordingly.

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 fatigue test method for towing and take-off of an outer cylinder strut joint of an aircraft front landing gear. Background technique [0002] In order to ensure the load-carrying capacity and life requirements of the nose landing gear used for towing take-off in marine environment, the structural form and load-carrying capacity of the nose landing gear are obviously strengthened. The nose landing gear needs to bear a large traction load, and the vertical load is about More than 2 times of that, and the landing gear strut joints need to bear the full traction load. As a newly designed landing gear, if the full-size landing gear is directly used for fatigue tests, there are disadvantages such as long production and manufacturing cycles of test pieces, long test bench design and manufacturing cycles, long test cycle...

AI Technical Summary

Problems solved by technology

As a newly designed landing gear, if the full-size landing gear is directly used for fatigue tests, there are disadvantages 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 the subsequent change cycle. longer

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