| 基于头舵联动控制的主动段减载技术 |
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| 引用本文： | 王晓雷,钟震,李强,张静,马上.基于头舵联动控制的主动段减载技术[J].导弹与航天运载技术,2021,7(1):68-71. |
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| 作者姓名： | 王晓雷 钟震 李强 张静 马上 |
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| 作者单位： | 北京宇航系统工程研究所，北京，100076 |
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| 摘 要： | 为了有效降低火箭在主动段飞行期间的横向载荷，提出一种基于头部空气舵与发动机喷管联动控制的主动段减载设计技术。该技术已在某型火箭设计中成功应用，计算结果显示采用这种减载设计能使火箭主动段飞行的全箭最大弯矩降低30%以上。对于有头部空气舵的固体火箭而言，该技术具有成本低、方便实现的特点。
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| 关 键 词： | 火箭 主动段 减载技术 空气舵 |
A Load-relief Technology Based on Auxiliary Control of Warhead Air Rudders for a Rocket in Ascent Stage |
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| Wang Xiao-lei,Zhong Zhen,Li Qiang,Zhang Jing,Ma Shang.A Load-relief Technology Based on Auxiliary Control of Warhead Air Rudders for a Rocket in Ascent Stage[J].Missiles and Space Vehicles,2021,7(1):68-71. |
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| Authors: | Wang Xiao-lei Zhong Zhen Li Qiang Zhang Jing Ma Shang |
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| Affiliation: | (Beijing Institute of Astronautical Systems Engineering,Beijing,100076) |
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| Abstract: | A load-relief control technology of rocket in ascent stage is proposed,which adopts combination control of warhead air rudders and Jet nozzle.This technology can effectively reduce the transverse flight load of a rocket.It is realized in a solid rocket design.And simulation shows that the max flight bending-moment in ascent stage is decreased about 30%.For a solid rocket with warhead air rudders,the load-relief control technology is simple and easy to implement. |
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| Keywords: | rocket ascent stage load-relief control air rudder |
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