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探索了固液火箭发动机作为上面级动力系统的性能特点;采用气瓶、贮箱和燃烧室并联布局的结构,有效减少了固液火箭发动机的长细比;建立了固液火箭发动机系统设计的数学模型,采用多岛遗传算法,开展了并联式固液火箭发动机总体方案的设计优化;优化结果与某固体火箭发动机上面级的比较说明,固液火箭发动机在上面级动力系统中具有较大的应用潜力。
The performance characteristics of the solid-liquid rocket motor as a top-level power system are explored. The structure of the parallel arrangement of gas cylinder, tank and combustion chamber is adopted to effectively reduce the slenderness ratio of the solid-liquid rocket engine. The solid-liquid rocket engine system design The mathematical model and the multi-island genetic algorithm are used to design and optimize the overall scheme of the parallel solid-liquid rocket motor. The comparison of the optimization results with that of a solid rocket motor shows that the solid-liquid rocket motor has larger Application potential.