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Traction taking-off fatigue test method of nose landing gear external cylinder suspension joint of aircraft

A fatigue test, nose landing gear technology, applied in the direction of aircraft component testing, etc., can solve the problems of long test bench design and manufacturing cycle, long test piece production and manufacturing cycle, and long change cycle, so as to reduce development risk and development cost, shorten The effect of development cycle

Inactive Publication Date: 2018-06-15
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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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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  • Traction taking-off fatigue test method of nose landing gear external cylinder suspension joint of aircraft
  • Traction taking-off fatigue test method of nose landing gear external cylinder suspension joint of aircraft
  • Traction taking-off fatigue test method of nose landing gear external cylinder suspension joint of aircraft

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Embodiment Construction

[0021] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0022] The following is a further detailed description of the aircraf...

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Abstract

The invention provides a traction taking-off fatigue test method of a nose landing gear external cylinder suspension joint of an aircraft. The traction taking-off fatigue test method comprises the following steps that a static strength test is conducted on an external cylinder suspension joint test sample piece; a fatigue test is conducted, wherein loads in the X, Y and Z directions are loaded coordinately by adopting a sine wave cyclic loading mode with the stress ratio being 0.06 and the loading frequency being 2 Hz; the fatigue test is conducted by being divided into two stages that in thefirst stage, the load loading cyclic frequency is 7500 times, one-time visual check is conducted every 500 times, if a fatigue damage phenomenon occurs, the test is stopped, parameters are recorded, otherwise the test piece is subjected to crack detection, and the test piece enters into the second stage after being detected to be qualified; and in the second stage, the load loading cyclic frequency is 7500-15000 times, one-time visual check is conducted every 500 times, if the fatigue damage phenomenon occurs, the test is stopped, parameters are recorded, otherwise the test is continued untilthe ending, and cyclic times is recorded. According to the fatigue test method, the fatigue performance and the life of a partial structure are testified in advance by testing the test piece, and thedevelopment cost is lowered.

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 aircraft nose landing gear outer tube suspension joint. 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 suspension joint of the landing gear needs 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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 李志鹏吴斌王向明苑强波吕伟
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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