| 基于遗传算法的固体火箭发动机参数优化设计 |
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| 引用本文： | 何景轩,田维平,何国强,余贞勇.基于遗传算法的固体火箭发动机参数优化设计[J].固体火箭技术,2004,27(4):250-254. |
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| 作者姓名： | 何景轩 田维平 何国强 余贞勇 |
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| 作者单位： | 中国航天科技集团公司四院,西安,710025;西北工业大学航天学院,西安,710072 |
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| 摘 要： | 基于连续型遗传算法,并与工程设计方法及相关结构有限元计算结果紧密结合,建立了固体发动机优化模型。以固体发动机的冲质比为目标函数,对发动机工作压强、喷管扩张比和喉径等参数进行了优化设计。计算结果表明,采用遗传算法十分有效,能够快速获得最优解,提高发动机的整体性能。
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| 关 键 词： | 固体推进剂火箭发动机 遗传算法 优化设计 |
| 文章编号： | 1006-2793(2004)04-0250-05 |
| 修稿时间： | 2003年12月15 |
The genetic algorithm for solid rocket motor parameter optimal design |
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| HE Jing-xuan,TIAN Wei-ping,HE Guo-qiang,YU Zhen-yong.The genetic algorithm for solid rocket motor parameter optimal design[J].Journal of Solid Rocket Technology,2004,27(4):250-254. |
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| Authors: | HE Jing-xuan TIAN Wei-ping HE Guo-qiang YU Zhen-yong |
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| Institution: | HE Jing-xuan~1,TIAN Wei-ping~1,HE Guo-qiang~2,YU Zhen-yong~11.The Fourth Academy of CASC,Xi'an710025,China, 2. Coll. of Astronautics,Northwestern Polytechnical University,Xi'an710072,China. |
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| Abstract: | By using continuous genetic algorithms, and results of finite element analysis and the engineering design, the optimization model was established for design of solid rocket motors(SRM). Total impulse to total mass ratio was taken as the objective function and the pressure, nozzle expansion ratio and diameter of nozzle throat etc. as optimization design variables. The optimization results showed that the genetic algorithms is superior efficient and SRM with better performance can be realized. |
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| Keywords: | solid propellant rocket engine genetic algorithm (GA) optimal design |
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