Abstract: 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.

Key words: propulsion system of aviation and aerospace, solid rocket motor, optimum design, multidisciplinary design optimization, individual discipline feasible strategy