针对于列装部队服役产品现场开展固体火箭发动机燃烧室界面粘接质量无损检测

In response to the demand for non-destructive testing of the bonding quality of the solid rocket motor combustion chamber interface on the field of service products in the field, a non-destructive testing for the debonding defect of the propellant/liner/insulation layer interface of the large solid rocket motor combustion chamber has been developed. system. The system is based on the electromechanical impedance frequency response function method, which is composed of multi-channel high-speed data acquisition equipment, piezoelectric active and passive sensor wafers, excitation device and software evaluation system. The excitation device is used to knock the surface of the solid engine shell to be measured through LabVIEW. The response signal is measured by the data acquisition program, and the interface debonding defect is judged according to the characteristics of the electromechanical impedance frequency response waveform and the number of crests. When the combustion chamber insulation/liner/propellant interface structure is intact, the frequency response function curve has only one obvious smooth The main wave peak, when the combustion chamber insulation layer/lining/propellant interface has a debonding defect, the number of wave peaks in the frequency response function curve increases, showing a clear sawtooth wave shape. This method is convenient and efficient, and is very suitable for the rapid field inspection of the bonding quality of the combustion chamber interface of the overall product after the final assembly of a large solid rocket motor, and it can also be used for long-term health monitoring of the combustion chamber interface state.

In view of the need to carry out non-destructive testing of solid rocket engine combustion chamber interface in the field of service products of the listed troops, a non-destructive detection system for deadhesive defects in the combustion chamber of large solid rocket engine combustion chamber is developed. Based on the machine resistance frequency response function method, the system consists of multi-channel high-speed data acquisition equipment, psychic main passive sensing wafer, excitation device and software evaluation system, and uses the excitation device to knock on the surface of the solid engine housing to be measured, and measures the response signal through the LabVIEW data acquisition program, according to the characteristics of the machine resistance anti-frequency waveform and the number of peaks. Interface de-adhesive defects, when the combustion chamber insulated layer / lining / propellant interface structure is intact, the frequency function curve has only a significantly smooth main peak, when the combustion chamber insulated layer / lining / propellant interface de-adhesive defects, the frequency function curve of the number of peaks increased, showing a clear jagged wave shape. This method is convenient and efficient, very suitable for large solid rocket engine assembly after the overall product combustion chamber interface bonding quality of the rapid field inspection, but also for long-term combustion chamber interface health monitoring.

In order to meet the requirement of nondestructive testing for interface bonding quality of solid rocket motor combustor in the field of military products, a nondestructive testing system for interface debonding defects of propellant / liner / insulation of large solid rocket motor combustor was developed. Based on the method of frequency response function of electromechanical impedance, the system is composed of multi-channel high-speed data acquisition equipment, piezoelectric active and passive sensing chip, excitation device and software evaluation system. The excitation device is used to knock on the surface of the structure to be tested of the solid motor shell. The response signal is measured by LabVIEW data acquisition program, and the interface disconnection is judged according to the characteristics of frequency response waveform of electromechanical impedance and the number of wave peaks When the structure of the combustion chamber insulation / liner / propellant interface is in good condition, the FRF curve has only one obvious smooth main wave peak. When the interface of the combustion chamber insulation / liner / propellant has debonding defects, the number of wave peaks of the FRF curve increases, showing an obvious sawtooth shape. This method is convenient and efficient, which is very suitable for the rapid field investigation of the interface bonding quality of the whole product combustion chamber after the assembly of large solid rocket motor, and can also be used for long-term health monitoring of the combustion chamber interface.<BR>