为了寻求喷管最佳扩张比,以提高固体发动机总体性能,结合发动机设计理论和工程设计方法,借助数值计算和编程工具,提出了以固体发动机的冲质比为目标函数的喷管扩张比寻优算法,并建立相应的数学模型。结果表明该算法能快速获得最优解,使发动机冲质比达到最大。该算法合理可行,实用性好,完善了固体发动机设计方法,也为后续研究拓展了思路。

Combined with solid propellant rocket motor design theory and engineering practice, numerical calculation method and programming were used, the impulse weight ratio was set as the objective function, a nozzle optimal divergence ratio optimization algorithm was proposed. The result shows that the algorithm is reasonable and feasible, which improves the solid rocket design method.