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Vertical wing loading method for full scale fatigue test

A fatigue test and vertical loading technology, which is applied in the field of aviation fatigue test, can solve the problems of lack of design methods, etc., and achieve the effect of saving test cost, shortening test period, and overcoming uncontrollable errors

Inactive Publication Date: 2019-03-19
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The purpose of the present invention is: in order to solve the technical problem of the lack of an effective design method when the full-scale fatigue test wing is vertically loaded, provide a full-scale fatigue test machine based on the weighted pressure center of multiple load conditions Wing Vertical Loading Method

Method used

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  • Vertical wing loading method for full scale fatigue test
  • Vertical wing loading method for full scale fatigue test
  • Vertical wing loading method for full scale fatigue test

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Embodiment Construction

[0024] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0025] Such as figure 1 Shown is the flow chart of the design method for wing vertical loading for full-scale fatigue tests. The parameters used in the examples are given. Specific steps are as follows:

[0026] Step 1. According to the test assessment requirements, the figure 2 The shown wing is divided into five assessment sections according to the ribs, and each assessment section is 3 ribs, 7 ribs, 10 ribs, 13 ribs and 16 ribs. The error of shear force and bending moment at the third rib of the outer wing root rib is required to be 0 to ensure the accuracy of wing load transmission; the shear force and bending moment error requirements of the other assessment sections are respectively 3% for shear force and 2% for bending moment %. The assessment section is generally divided into 3-4 ribs. If there are too many ribs, the loading error will be large....

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Abstract

The invention belongs to the field of aviation fatigue test and in particular relates to a vertical wing loading method for a full scale fatigue test. The method disclosed by the invention comprises the following steps: performing weighting on a pressure core under multiple load conditions according to the damage degree, and determining the position of a loading actuator cylinder. The vertical wing loading method for the full scale fatigue test provided by the invention is obtained on premise of meeting requirements of shear force, bending moment, torque and design load conditions of each control plane of the wings, and can be widely applied to designing vertical wing loading points for the full scale fatigue test of various aircrafts.

Description

technical field [0001] The invention belongs to the field of aviation fatigue tests, in particular to a wing vertical loading method for full-scale fatigue tests. Background technique [0002] The full-scale fatigue test of an aircraft is a key link in determining the life of the aircraft, involving many fatigue load conditions and a long test duration, often lasting several years or even more than ten years. The difference from the static strength test is that during the fatigue test, in order to ensure the progress of the test, only one set of loading system and fixtures are generally used for the test, and the test will not be changed according to different working conditions. The resulting problem is that it is difficult for a loading system to meet the loading accuracy requirements of most load cases, resulting in large errors. The wing is the key component of the aircraft and bears most of the vertical load of the aircraft. If the error cannot be guaranteed, the test ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/32
CPCG01N3/32G01N2203/0073
Inventor 张彦军朱亮宁宇秦剑波王新波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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