推进技术 ›› 1993, Vol. 14 ›› Issue (3): 16-21.
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方国尧,王庆,高山辉
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摘要： 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。
关键词: 固体火箭发动机;喷管;最佳设计
Abstract: In order to design optimum nozzle for air-air missile solid rocket motor, the mass model of solid rocket motor, the nozzle specifice impulse model of solid rocket motor and the objective function are established. Five different type of nozzles are choosen lor calculation: Conical, parabolidal,two different arcs,quadiatic polynominal and cubic polynominal. The optimization results show that the models established are correct. The method can be used as a referece for others nozzle design.
Key words: Solid rocket engine;Nozzle;Optimum design
方国尧,王庆,高山辉. 火箭发动机喷管内型面优化设计[J]. 推进技术, 1993, 14(3): 16-21.
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