AP-CMDB推进剂燃速压强指数的变化分析与辨识

Analysis and discrimination of the burning rate pressure exponent of AP-CMDB propellants

采用燃烧模型分析了AP CMDB推进剂的燃速压强指数与推进剂配方组成和火箭发动机燃烧室压强之间的耦合关系,指出了该推进剂的燃速压强指数随AP颗粒和双基母体的燃速差而变化,对于确定配方组成的AP CMDB推进剂,则该指数将主要随压强而变化,且近似呈对数关系。采用C K法对特定配方进行了压强指数辨识,辨识结果能够较准确地预示脉冲推力器的内弹道性能。

The coupling relations of the burning rate pressure exponent of AP-CMDB propellants with the propellant formulation and the pressure in rocket chamber were analyzed by using the combustion model. The results indicate that the burning rate pressure exponent varies with the difference of burning rate between AP particles and the matrix DB propellant. For a defined AP-CMDB formulation, the burning rate pressure exponent varies mainly with the pressure as a logarithmic function of pressure. By the C-K method, the burning rate pressure exponent of a particular AP-CMDB propellant is discriminated and compared with the test data. The results can be used to predict the internal ballistic performance of rocket motor.