短时间工作发动机内弹道计算方法

Investigation on the Calculating Method for Short Time Working Solid Rocket Motor

为了提高短时间工作固体火箭发动机的内弹道计算精度,对现有固体发动机内弹道性能计算方法进行适应性修改,建立了适用于短时间工作固体发动机的高精度内弹道计算方法。通过预示内弹道性能与实测发动机试验数据的对比,修改后计算方法的预示精度在±5%以内,计算精度显著提高。计算结果表明,在发动机平衡段,喷管效率和理论推力系数基本保持不变,可以为短时间工作发动机的设计提供依据。

In order to increase the calculation accuracy of performance for short time working solid rocket motor, a method is established by modifying the conventional one. The analysis of calculation and test results show that the calculation accuracy is not more than ±5 percent, which means that the accuracy of calculation is improved significantly. The calculation results show that nozzle efficiency and theoretical thrust coefficient will remain unchanged when working in high pressure. This calculation method can provide an important reference for the design of short time working solid rocket motor.