基于固体火箭发动机工作原理的两种推进剂燃速测试方法对比OA北大核心CSTPCD

In response to the challenge of efficient on the high-pressure dynamic burning rates of solid propellants testing,the impulse method and the mass flow rate method were respectively employed to measure the burning rates of two kinds of solid propellants under different pressures.The results show that in the pressure stable section caused by severe nozzle erosion,the burning rates obtained by the impulse method in three different time periods are 17.92,18.00,and 18.04mm/s,demonstra-ting the good consistency between individual testing results.The mass flow rate method is simple but yields unreasonable results due to the severe nozzle erosion.Results of parallel experiments of the two kinds of propellants indicate that the burning rate test results obtained by the impulse method have small deviations,with a maximum deviation of less than 0.3mm/s for com-posite propellants at 8-35MPa and 0.4mm/s for double base propellants at 8-25MPa,indicating that the burning rates ob-tained by mass flow rate method exhibite larger deviations.Nozzle erosion does not affect the burning rate results obtained by impulse method,and it can reduce the pressurization rate in the high-pressure stage,facilitating an instantaneous response of the burning rate to changes in pressure.The burning rates of composite propellants tested at 20MPa by using the impulse meth-od were 22mm/s and 21.96mm/s,with a maximum error of 0.45％compared to the standard motor method.