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A verification test method for joint loading of aircraft body and landing gear

A technology of joint loading and verification test, applied in the testing of machine/structural components, measuring devices, instruments, etc., can solve the problems of unverifiable, high center of gravity overload, large sinking rate, etc., to shorten the test progress and improve the test The effect of efficiency

Active Publication Date: 2016-08-24
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

For example, for a fixed platform take-off and landing aircraft on water, its sinking rate is high and its center of gravity is overloaded at the moment of landing. Other structures of the airframe have a great influence, and this kind of load situation belongs to the load of the landing gear components, which cannot be verified in the whole machine test

Method used

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  • A verification test method for joint loading of aircraft body and landing gear
  • A verification test method for joint loading of aircraft body and landing gear

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Embodiment Construction

[0013] The present invention will be described in further detail below through specific embodiments and in conjunction with the accompanying drawings.

[0014] First, draw the shear force and bending moment diagram of the aircraft under the whole machine load and the landing gear load, see the attached figure 1 , attached figure 2 . The drawing data is the finite element calculation result of the whole machine, and the drawing tool is Excel2007. The internal force caused by the landing gear load in the figure is locally greater than the internal force caused by the aerodynamic load of the whole machine, so it is necessary to take the landing gear load as a load case in the static test of the whole machine.

[0015] Second, the design of the loading scheme. In the static test of the whole aircraft, the landing gear load is taken as a test load situation, and the loading scheme is designed separately according to the landing gear load. The load trim adopts the multi-point c...

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Abstract

The invention belongs to the field of airplane design and relates to a method for a verification test of combined loading of an airframe and an undercarriage. The method is characterized in that firstly, assessment of a load is conducted; secondly, a loading scheme is designed; thirdly, loading is tested; the load of the undercarriage serves as an examination working condition of a full-aircraft static test, combined loading of the airframe and the undercarriage is achieved in the full-aircraft static test, and an airframe structure static strength design envelope under the special working condition of the undercarriage can be fully verified.

Description

technical field [0001] The invention belongs to the field of aircraft design and relates to a verification test method for combined loading of an aircraft body and landing gear. Background technique [0002] In the process of aircraft design, in order to check whether its strength meets the design requirements, it is necessary to carry out static tests. The static test of the aircraft is further divided into the whole aircraft static test and the component static test according to the assessment site and test scale. The static test of the whole machine mainly evaluates the overall strength reserve of the airframe structure under various load conditions of the whole machine, and the static test of components mainly evaluates the strength reserve of the specific structure of the airframe under the action of local loads. Usually, the load of the component static test will not cause static damage to the aircraft skeleton structure or important connection parts, so the whole mac...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M99/00
Inventor 曹奇凯靳诚忠何刚王远鹏王鄢
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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