中小型固体火箭发动机喷管扩张比寻优算法

Optimization Algorithm of Small and Medium-sized Solid Rocket Motors Nozzle Optimal Divergence Ratio

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.