Nondestructive testing method for debonding defects of solid rocket engine interface
A solid rocket and non-destructive testing technology, which is applied in the direction of using sound waves/ultrasonic waves/infrasonic waves to analyze solids, measuring devices, and processing detection response signals, etc. It can solve problems such as low detection efficiency, difficulty in covering all detection parts, multiple safety and quality risks, etc.
Inactive Publication Date: 2019-09-17
XIAN AEROSPACE CHEM PROPULTION PLANT +1
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[0010] In order to overcome the shortcomings of low detection efficiency, complex operation, more safety and quality risks, and difficulty in covering all detection parts in the prior art, the present invention proposes a non-destructive detection method for interface debonding defects of solid rocket motors
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Embodiment Construction
[0056] This embodiment is a mobile and fast non-destructive detection method for the interface debonding defect of a certain solid rocket motor propellant / lining layer / insulation layer. The diameter of the detected engine is 2000mm, the shell material is composite fiber material, and the internal structure of the shell is as follows: For rubber insulation materials, lining materials and composite solid propellants, the quality of the interface between various materials is required to be well bonded.
[0057] The specific implementation process is:
[0058] Step 1: Sensor measurement and pasting
[0059] Use a multimeter to confirm and measure the capacitance of all the lead zirconate titanate sensors, and the confirmation standard is that the capacitance of each sensor should be 2.5nF±30%. If the measurement results do not match, it will not be used.
[0060] According to the design requirements, mark the sensor sticking position in the detection area of the engine casing....
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Abstract
The invention relates to a nondestructive testing method for debonding defects of a solid rocket engine interface, and the method combines an electromechanical impedance method and a frequency response function method and is used for testing a solid rocket engine combustion chamber interface. The method comprises the following steps of forming a detection system by using a universal equipment NI multi-channel high-speed data acquisition device, a PCB force hammer, a sensor and the like; knocking the surface of a structure to be detected by using the force hammer to provide a pulse-shaped force; and measuring a time domain waveform of a response signal through a signal acquisition program to obtain a frequency response function curve of an engine heat insulation layer / lining layer / propellant interface so as to judge whether the interface structure is intact. The method is used for the flexible and rapid nondestructive detection of the debonding defects of the interface of the solid rocket engine propellant / lining layer / heat insulation layer of the composite fiber material with the diameter of about 2000 mm, particularly for an integrally assembled product, the detection can be realized on a storage site without decomposition, the method has the characteristics of convenience and high efficiency, and the nondestructive testing method is suitable for the rapid inspection of the debonding defects of the interface of the integrally assembled product.
Description
technical field [0001] The invention relates to the field of non-destructive testing, in particular to a non-destructive testing method for rapid screening of debonding defects at the interface of solid rocket motor propellant / lining layer / thermal insulation layer. Background technique [0002] At present, there are only two non-destructive testing methods for solid rocket motor propellant / lining interface / insulation layer interface debonding defects in China, depending on the shell material, radiography and ultrasonic testing. [0003] (1) For solid rocket motors whose casing materials are non-metallic fiber materials, the debonding defects at the interface of propellant / lining / insulation layer can only be detected by radiography. Chemical Dynamics Co., Ltd. has used radiography for the actual detection of various types of engine propellant / lining / insulation interface decades ago. Radiation detection generally uses an electron linear accelerator with an energy of 1 to 15 M...
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IPC IPC(8): G01N29/04G01N29/44
CPCG01N29/045G01N29/4472G01N2291/0256G01N2291/2694
Inventor 白小平屈文忠王正安余治平肖黎谢学多孙博赵仕通张小花王刚胡子衍张守诚黄伟健刘宾焦阳
Owner XIAN AEROSPACE CHEM PROPULTION PLANT
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