| 高速旋转弹的姿态控制系统设计 |
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| 引用本文： | 贾正望,郭治.高速旋转弹的姿态控制系统设计[J].火炮发射与控制学报,2011(3). |
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| 作者姓名： | 贾正望 郭治 |
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| 作者单位： | 南京理工大学自动化学院,江苏南京,210094 |
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| 基金项目： | 国家自然科学基金(60804019) |
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| 摘 要： | 为了解决高速旋转弹姿态控制的难题,设计了一种基于滑动质量块姿态控制系统。从高速旋转弹姿态特点分析出发,建立了姿态动力学方程。根据时间尺度对其姿态回路进行了时标分离,将其分为内外两个回路,分别进行了控制系统设计。外环设计了含有跟踪误差及其积分函数的滑模控制器,内环则采用了依赖于状态的黎卡提方程(SDRE)的最优控制器。仿真结果表明,该控制系统能快速有效地实现对弹体姿态控制,可为实际工程应用提供必要的借鉴。
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| 关 键 词： | 航天器结构与设计 姿态控制 滑动质量块 高速旋转 |
Attitude Control System Design for High Speed Rotation Missile |
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| JIA Zheng-wang,GUO Zhi.Attitude Control System Design for High Speed Rotation Missile[J].Gun Launch & Control Journal,2011(3). |
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| Authors: | JIA Zheng-wang GUO Zhi |
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| Affiliation: | JIA Zheng-wang,GUO Zhi (School of Automation,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu China) |
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| Abstract: | To solve the attitude control of high speed rotation missile,the moving mass attitude control system was designed.Based on high speed rotation missile characteristic,the moving mass layout optimization situation was deployed.The dynamic equation was established.Two loop attitude control strategy was present.The sliding hyperplane containing tracking error and intergral function was designed in outer loop.The control law based on state depended Riccati eauation was applied in inner loop.Finally,the simulatio... |
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| Keywords: | spacecraft structure and design attitude control moving-mass high speed rotation |
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