In order to deal with the complexity of optimum design for solid rocket motors ( SRM) , the way of multidisciplinary design optimization analyzed the complicated system was introduced. Taking optimum design for SRM with star perforation grain for instance, the design model was partitioned into several subsystems whose functions were defined in accordance with the design requirements and the respective computation models were provided. Subsequently the coupling relationship between subsystems was analyzed in a manner of multidisciplinary design optimization. Finally the instrumental variables were introduced to decouple subsystems from each other by the individual discipline feasible strategy and the optimization variables of concurrent design for SRM were determined. The feasible sequential quadratic programming was selected to optimize the resulting problem and the calculation example has verified the validity of this design pattern. Such a pattern can take full use of modularized and parallel design, so it is helpful to improve the optimization efficiency and model versatility and provides a preferable method to optimum design for SRM involving more comprehensive design factors.%针对固体火箭发动机优化设计的复杂性,以星孔装药发动机优化设计为例,采用多学科设计优化分析复杂系统的思想,将发动机设计模型子系统化,并根据设计要求规定各个子系统的相应功能,给出各个子系统的计算模型;采用多学科设计优化的概念和方法分析子系统间的耦合关系;采用单学科可行法策略引入辅助设计变量使各个子系统解耦,进而确定发动机模型并行设计的优化设计变量,并选用可行序列二次规划优化算法进行求解.计算实例验证了这种设计模式的有效性.该设计模式充分考虑发动机的模块化并行设计,有利于提高优化效率以及模块的通用性,对于考虑设计因素比较全面的发动机优化设计提供了一种很好的方法.
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