摘要
针对太阳帆航天器挠性模态易激发但难测量的问题,该文研究以控制杆作为执行机构的太阳帆航天器姿态控制。基于控制杆的动力学分析建立了太阳帆俯仰轴刚柔耦合模型。提出了1种姿态机动路径柔化与可测刚体姿态信息反馈控制相结合的太阳帆姿态控制方法。设计了比例积分型状态误差反馈律,并给出了使系统刚体姿态与挠性模态均渐近稳定的充分条件。仿真结果表明,所提控制方法能较好地满足太阳帆姿态调整的快速性与准确性要求。
Due to the problem of solar sails that it is easy to excite but difficult to detect the flexible modes,an attitude control method for a solar sail is studied using a gimbal boom as the actuator .A rigid-flexible coupling model for the pitch axis is established with the dynamics of the gimbal boom . A novel attitude control method is proposed combining a path planning method with a measurable -rigid-information feedback controller .A proportion-integral（PI）state error feedback control law is de-signed ,and an asymptotical stabilization condition for both rigid states and flexible modes is given . The numerical simulation results demonstrate the proposed control method can satisfy the rapidity and accuracy of attitude adjustment for solar sails .
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2016年第3期272-277,共6页
Journal of Nanjing University of Science and Technology
基金
国家自然科学基金(61473152)
关键词
太阳帆
姿态控制
控制杆
俯仰轴
刚柔耦合模型
挠性模态
反馈控制
比例
积分
状态误差
solar sails
attitude control
gimbal boom
pitch axis
rigid-flexible coupling model
flexible modes
feedback control
proportion
integral
state error
