升力式再入飞行器体襟翼姿态控制方法

王之; 李惠峰; 包为民

doi:10.13700/j.bh.1001-5965.2015.0192

升力式再入飞行器体襟翼姿态控制方法

doi: 10.13700/j.bh.1001-5965.2015.0192

王之¹,
李惠峰^1, ,,
包为民^1,2

1.
北京航空航天大学宇航学院, 北京 100083
2. 中国航天科技集团公司, 北京 100048

基金项目: 国家自然科学基金(61174221,11272062)

详细信息

作者简介:
王之男,博士研究生。主要研究方向:高超声速飞行器动力学与控制技术。Tel.:010-82339527 E-mail:bjwangz@buaa.edu.cn;李惠峰女,博士,教授,博士生导师。主要研究方向:高超声速飞行器制导与控制技术。Tel.:010-82339276 E-mail:lihuifeng@buaa.edu.cn

通讯作者:
李惠峰,Tel.:010-82339276 E-mail:lihuifeng@buaa.edu.cn

中图分类号: V448.2
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出版历程
- 收稿日期: 2015-04-02
- 网络出版日期: 2016-03-20

Body-flap attitude control method for lifting re-entry vehicle

WANG Zhi¹,
LI Huifeng^{1
, ,},
BAO Weimin^1,2

1.
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2. China Aerospace Science and Technology Corporation, Beijing 100048, China

Funds: National Natural Science Foundation of China (61174221, 11272062)

摘要

摘要: 针对升力式再入飞行器体襟翼控制三通道时的非最小相位问题,设计了一种姿态输出跟踪控制方法。选择合理的局部微分同胚,将姿态输入-输出模型转换为正则形式并得到内动态。通过对内动态进行稳定性分析并提出系统非最小相位特性的判据,采用此判据可判定当存在副翼反效时该输出跟踪控制问题为非最小相位控制问题。针对该问题,首先依据内动态与外部动态的线性相关度将正则模型分解为最小相位子系统(纵向通道)和非最小相位子系统(横侧向通道),然后运用动态逆控制技术对2个子系统分别设计状态反馈控制器,最后基于Lyapunov方程和最小范数控制策略在非最小相位子系统中引入非线性辅助控制项以镇定整个姿态控制回路。仿真结果表明了在仅有体襟翼控制的情况下该控制方法能够精确跟踪控制指令并镇定内动态。
- 升力式再入飞行器 /
- 体襟翼姿态控制 /
- 非最小相位特性判据 /
- 副翼反效 /
- 最小范数控制策略
Abstract: An attitude output tracking control method is proposed for a lifting re-entry vehicle with a non-minimum phase property. Such problem is caused by body flaps which are the only actuators to be used for controlling three-channel. By using local differential homeomorphism, the attitude input-output model is transformed into normal form, and internal dynamics are obtained. A criterion of non-minimum phase is developed by analyzing the internal dynamics' stability, and this criterion is used to predict the non-minimum phase phenomena when aileron reversal exists. To solve this problem, the normal form is decomposed into a minimum phase subsystem (longitudinal channel) and a non-minimum phase subsystem (lateral-directional channel). And then, dynamics inversion is used to design the state-feedback controllers for these two subsystems.Moreover, a nonlinear auxiliary control input is introduced to stabilize the overall attitude control loop by both Lyapunov function and a minimum-norm control strategy. Simulation results demonstrate that in the case where body flap actuators are employed for attitude control, the control commands can be tracked and internal dynamics can be stabilized by the proposed method.
- lifting re-entry vehicle /
- body-flap attitude control /
- criterion of non-minimum phase /
- aileron reversal /
- minimum-norm control strategy

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