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A method for measuring thermal stress of a metal-composite hybrid structure for aircraft

A technology of composite materials and hybrid structures, applied in the direction of measuring force, measuring devices, electromagnetic measuring devices, etc., can solve the problems of increasing structural weight, safety risks, etc., and achieve the effect of improving precision, improving accuracy, and good measurement effect

Active Publication Date: 2022-07-15
CHINA AIRPLANT STRENGTH RES INST
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

This way of dealing with thermal stress will inevitably lead to a large deviation between the results of the structural strength verification test and the actual use situation. In the conservative case, the structural weight will be increased unnecessarily, and in the dangerous case, it will bring safety risks.

Method used

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  • A method for measuring thermal stress of a metal-composite hybrid structure for aircraft
  • A method for measuring thermal stress of a metal-composite hybrid structure for aircraft
  • A method for measuring thermal stress of a metal-composite hybrid structure for aircraft

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Embodiment Construction

[0061] like Figure 1 to Figure 4 Shown is a method for measuring thermal stress of a metal-composite hybrid structure for aircraft, the method comprising the following steps:

[0062] The method includes the following steps:

[0063] Step 1. Obtain test specimens and standard specimens according to the metal-composite hybrid structure for aircraft:

[0064] Step 101, taking the part to be tested on the aircraft as a test specimen; wherein, the test specimen is a metal-composite hybrid structure;

[0065] Step 102, preset multiple test points on the surface of the test specimen;

[0066] Step 103, making a 200mm×200mm square test piece as a standard test piece; wherein, the standard test piece and the material at the test point on the test test piece are the same;

[0067] Step 2. Calibration of the sensitivity coefficient of the strain gauge:

[0068] The strain gauge was calibrated by the equal-strength beam experimental device, and the calibrated sensitivity coefficient...

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Abstract

The invention discloses a method for measuring thermal stress of a metal-composite material hybrid structure for aircraft. The method comprises the following steps: 1. Obtaining a test specimen and a standard specimen according to the metal-composite material hybrid structure for an aircraft; 2. Strain The calibration of the sensitivity coefficient of the sheet; 3. The thermal output measurement of the standard specimen; 4. The total strain measurement of the test specimen; 5. The thermal stress acquisition of the metal-composite hybrid structure for aircraft. The method of the invention has simple steps and reasonable design. By correcting the total strain at the test point in the test specimen under the measurement temperature, the thermal strain at the test point in the test specimen under the measurement temperature is obtained, and then the thermal stress at the test point is obtained. , in order to improve the accuracy of thermal stress measurement of aircraft metal-composite hybrid structures.

Description

technical field [0001] The invention belongs to the technical field of thermal stress testing of aircraft structures, in particular to a method for measuring thermal stress of a metal-composite hybrid structure for aircraft. Background technique [0002] Due to its higher specific strength and specific stiffness than metal materials, composite materials have been widely used in aircraft and other aircraft, and their proportion in aircraft structures has shown an increasing trend. Even so, composite materials cannot completely replace metal materials due to their strength and stiffness limitations. Therefore, in the design of aircraft structures, in order to take into account the requirements of structural strength and weight reduction, metal-composite hybrid structures with metal materials as the main load-bearing structure and composite materials as the secondary load-bearing structure and functional structure are widely used. For example, the thermal expansion coefficient...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01L1/22G01B7/16
CPCG01L1/2262G01B7/18
Inventor 刘海燕李闯勤李红贤白泽瑞任战鹏杜文辉吴敬涛
Owner CHINA AIRPLANT STRENGTH RES INST
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