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给出了带＂锥－柱形＂装药的旋转固体火箭发动机的一维内弹道计算方法，其燃速计算采用稳态分析方法，喷管流量计算采用等熵旋转喷管流的简化方法。所得结果和旋转试车台上实测的实验结果吻合较好。计算和实验表明，＂锥－柱形＂装药呈现较大的加速度效应。文中提供的计算方法具有较高预示精度，可推广到其它药四旋转发动机的内弹道计算，对旋转发动机设计具有指导作用。
A one-dimensional internal trajectory calculation method for a rotating solid rocket motor with “cone-cylindrical” charge is given. The steady-state analysis method is used to calculate the burning rate, and a simplified method of isokinetic nozzle flow is used to calculate the nozzle flow. The results obtained are in good agreement with the experimental results measured on a rotating test bench. Calculations and experiments show that the “cone-cylinder” charge exhibits a large acceleration effect. The calculation method provided in this paper has high predictive accuracy and can be extended to other ballistic computations of four-revolving engines, which can guide the design of revolving engines.