本文应用固体火箭发动机原理与准一元流动理论，在现有的内弹道方程基础上，建立了能对长尾管结构、多元推进剂组合装药及多元推进剂组合装药长尾管结构的单室固体火箭发动机内弹道进行计算的通用方程组，导出了平衡压力计算的通用公式。文中对多元推进剂装药长尾管结构发动机进行了实例计算，计算结果与实验结果符合得较好。

Based upon principles of solid propellant rocfcts and quasi-one dimen- tional flow theory, on the basis of interior ballistics a set of general purpose equations has been established. These equations can be used to calculate the interior ballistics of single chamber solid propellant rocket motors with long tail tubes or mnltiple propellant charges, or for motors with long tail tubes as well as mulitiple propellant charges. General pu- pose equations for calculating the equilibrium pressures have also been derived. Results of computation based on this method are in good agreement with experimental results.