Taking the dynamic burning rate technology of standard solid rocket motor(SRM)as the research object,the dynamic burning rate and pressure data of the SRM under the ignition condition of fixed ultrasonic velocity was tested by means of the ultra-sonic thickness measurement principle,and through the analysis of these data,a new dynamic combustion signal identification meth-od was proposed,the data of propellant regression thickness and time variation during the motor ignition were obtained.Finally,the ultrasonic velocity calibration model under different pressures at room temperature was established by experimental method,and the real-time ultrasonic velocity in the ignition process of the motor was calculated by combining the pressure data of the test process,which was substituted into the propellant regression thickness and time data obtained under the condition of fixed ultrasonic velocity,and the real-time burning rate of the motor during the ignition process was obtained by derivation.The results show that,the dynamic burning rate test method based on ultrasonic can realize the dynamic burning rate test of the whole motor and has high time resolu-tion accuracy.The error of combustion time calculated by ultrasonic dynamic burning rate test and traditional pressure-time curve is 0.235%.In addition,by comparing the pressure-time and dynamic burning rate-time curves after ignition,it is found that the trend of dynamic burning rate and pressure curves after the motor pressure is similar.
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