| 固体火箭发动机燃烧室压强及喷管扩张比优化设计 |
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| 引用本文： | 何景轩,甘晓松,乐发仁,余贞勇.固体火箭发动机燃烧室压强及喷管扩张比优化设计[J].固体火箭技术,2003,26(4):12-13. |
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| 作者姓名： | 何景轩 甘晓松 乐发仁 余贞勇 |
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| 作者单位： | 中国航天科技集团公司四院设计部,西安,710025 |
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| 摘 要： | 以固体火箭发动机冲质比为目标函数，采用复合形法优化技术，对在一定高度范围内工作的纤维缠绕壳体固体发动机的燃烧室平均压强和喷管扩张比进行了优化计算。该方法特别对第一级工作的发动机总体方案优化的初步设计具有重要的参考价值。
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| 关 键 词： | 固体推进剂火箭发动机 燃烧室 工作压强 喷管 扩张比 优化设计 |
| 文章编号： | 1006-2793(2003)04-0012-02 |
| 修稿时间： | 2002年9月4日 |
Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors |
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| HE Jing-xuan,GAN Xiao-song,YUE Fa-ren,YU Zhen-yong//The Design.Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors[J].Journal of Solid Rocket Technology,2003,26(4):12-13. |
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| Authors: | HE Jing-xuan GAN Xiao-song YUE Fa-ren YU Zhen-yong//The Design |
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| Institution: | HE Jing-xuan,GAN Xiao-song,YUE Fa-ren,YU Zhen-yong//The Design Department of the Fourth Academy of CASC,Xi'an710025,China. |
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| Abstract: | By setting the ratio of total impulse to loaded weight as the objective function, the chamber average pressure and nozzle area expansion ratio of solid rocket motors, which works in certain altitude range, are optimized with a complex optimizing technology. The method is useful in preliminary system concept optimization design of the first stage solid rocket motors. |
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| Keywords: | solid propellant rocket motors operating pressure area expansion ratio design optimization |
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