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根据平行层燃烧理论,推导了不同药型燃烧面积和燃烧边界长度随燃去肉厚变化的数学规律;在此基础上,建立了固液火箭发动机系统设计模型,将设计过程转化为数学模型;之后采用遗传算法对不同药型固液火箭发动机进行了优化设计.通过对优化结果的比较和分析,开展了不同药型应用于固液火箭发动机的性能特点及其机理的研究,指出了固液火箭发动机不同于固体火箭发动机的内弹道特性.
Based on the theory of parallel layer combustion, the mathematical laws of combustion area and combustion boundary length varying with burning and flesh thickness were deduced. On this basis, a solid-liquid rocket engine system design model was established and the design process was transformed into a mathematical model. After that, genetic algorithms were used to optimize the design of different types of solid-liquid rocket motors.By comparing and analyzing the optimization results, the performance characteristics and mechanism of different types of solid-liquid rocket motors were studied, Rocket engines are different from the internal ballistic characteristics of solid rocket motors.