Abstract: The design of the inner contour of solid propellant rocket motor nozzle is a key point to improve the efficiency of the nozzle. Based on Genetic Algorithms, a direct optimization method was used to optimize the key parameters determining the inner contour of the nozzle, to reduce the specific impulse loss and improve the efficiency of the engine. The specific impulse was obtained from two-phase flow calculation of the nozzle. Furthermore, a software interface was designed to automatically realize the contour optimization design for the general nozzle. As a result,good effect was obtained from the optimal computation for the current nozzle.

Key words: Nozzle contour optimization; Genetic Algorithms; Loss of the two-phase flow

摘要： 火箭发动机喷管内型面设计是喷管设计中的重要研究课题,是提高喷管效率的关键。采用基于遗传算法的直接优化设计方法对决定喷管内型面的关键参数进行优化,以减少喷管的比冲损失,提高发动机性能。比冲损失的大小通过喷管两相流计算获得,设计了相应的软件自动完成常见喷管的喷管型面优化设计,对现有型号喷管进行优化的计算结果表明,喷管的相对比冲损失可以显著减小。

关键词: 喷管型面优化;遗传算法;两相流损失