Abstract: The difference between the actual performance and the aim of design on solid rocket engine was analyzed.The object about the parameter adjustment on project was presented. Founded the mathematics model with combustor pressure as objective function, regarded the double conditions of performance and project as restriction.Based on the calculation optimization and analysis,the design parameters of motor were adjusted.

Key words: Solid propellant rocket engine;Motor performance parameter;Parameter optimization;Adjustment

摘要： 分析了固体火箭发动机研制阶段地面试验性能与设计目标之间存在偏差的原因 ,提出了工程上参数调整的对象 ,并以性能和工程双重条件作为约束 ,建立了以燃烧室压强为目标函数的数学模型。在优化计算、分析的基础上 ,进行发动机设计参数的调整。经工程实际验证 ,取得了较好的效果

关键词: 固体推进剂火箭发动机;发动机性能参数;参数最优化;调整