| 远程战术火箭控制方案研究 |
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| 引用本文： | 程养民,乐发仁.远程战术火箭控制方案研究[J].固体火箭技术,2003,26(4):1-5,17. |
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| 作者姓名： | 程养民 乐发仁 |
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| 作者单位： | 中国航天科技集团公司四院,西安,710025 |
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| 摘 要： | 按照由简到繁的顺序，提出三种控制方案并进行了弹道控制仿真计算，分析了各方案的弹道精度，研究适合远程战术火箭弹的控制方案及设计要求，并考察了固体姿控发动机作为执行机构的可行性，认为其具有不少优点，可以满足远程战术火箭的技术要求，但其质量仅略重于空气舵。
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| 关 键 词： | 远程战术火箭弹 弹道控制 设计 姿态控制 末制导 控制精度 |
| 文章编号： | 1006-2793(2003)04-0001-05 |
Study on the control projects of long range tactical rocket |
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| CHENG Yang-min,YUE Fa-ren//The Fourth Academy of CASC,Xi'an,China..Study on the control projects of long range tactical rocket[J].Journal of Solid Rocket Technology,2003,26(4):1-5,17. |
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| Authors: | CHENG Yang-min YUE Fa-ren//The Fourth Academy of CASC Xi'an China |
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| Institution: | CHENG Yang-min,YUE Fa-ren//The Fourth Academy of CASC,Xi'an710025,China. |
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| Abstract: | Based on the imitative trajectory caculation, three control projects and their accuracy are investigated to obtain suitable control projects and design requirements for a long range tactical missile. At the same time, the attitude control solid motor as the executive mechanism is studied and the result shows that it has some advantages and can meet the requirements of the long range tactical missile though it may be slightly heavier than the jet vane. |
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| Keywords: | rocket trajectory calculaiton attitude control terminal guidance |
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