以两种空-空导弹固体火箭发动机喷管作为算例,为此,建立固体火箭发动机的质量模型,喷管的质量比冲模型和目标函数模型,选择五种喷管扩散段内型面:锥形喷管,抛物线喷管,双圆弧喷管,二次多项式喷管和三次多项式喷管,进行优化设计,利用优化理论,成功地完成了五个设计变量的优化问题。优化结果表明,所建立的计算模型是正确的,并可用于其它大中型号的喷管设计。 Taking two kinds of air-to-air missile solid rocket motor nozzles as an example, a solid rocket motor mass model, a nozzle mass ratio impulse model and an objective function model are established. Five types of nozzle diffuser section inner profiles are selected: Cone nozzle, parabola nozzle, double circular nozzle, quadratic polynomial nozzle and cubic polynomial nozzle, to optimize the design, the use of optimization theory, the successful completion of the five design variables optimization problem. The optimization results show that the calculation model established is correct and can be used for nozzle designs of other large and medium-sized nozzles.