固体火箭发动机实际燃速常数的计算

CALCULATION OF ACTUAL BURNING RATE CONSTANT IN SOLID ROCKET MOTOR

关键词:  固体推进剂火箭发动机  推进剂燃速  参数识别  相关特性

Key words:  Solid propellant rocket engine  Propellant burning rate  Parameteridentification  Correlation property.

摘要:

根据试车数据，对全尺寸发动机和标准发动机瞬时燃速进行了计算。利用参数辨识技术，确定了维也里燃烧公式（ｒ＝ａｐｎ）里的常数。计算结果表明：对应用在不同发动机中的同一种推进剂来说，其燃速系数ａ和压强指数ｎ是不同的。探讨了不同发动机燃速常数变化的原因以及规律性。提供了分析全尺寸发动机、标准发动机之间燃速相关性的新方法。

Abstract:

Based on the data from the motors firing, the transient burning rateof the full-scale motor and the standard testing motors is calculated. By using thetechnique of parameter identification, the constants in the Vielie Burning Rate Formula is determined. The determined results show that burning rate coefficient andburning rate pressure exponent are not only relatied to propellant characteristic, butalso relatied to the motor parameters. So, the regularity and cause of variation of theburning rate coefficient and burning rate pressure exponent are analysed. And a newapproach to analyse the correlation between full-scale motor and the standard testing motor is provided. And, the result of calculation is in good agreement with expert mental result.