摘要
某些低轨道航天器在执行任务时 ,需要通过姿态控制系统使其有效载荷 (如星载相机 )在一段时间里连续指向地面或空间的给定目标。文中研究了带 3个反作用飞轮的低轨道航天器的姿态跟踪开展问题。首先根据刚体运动学知识推导出航天器的参考姿态角、参考角速度和参考角加速度表达式 ,然后基于卫星航天器姿态动力学给出了 3个互相垂直安装的反作用飞轮的控制律 ,并利用 L yapunov稳定性理论证明了闭环系统的渐近稳定性。
Spacecrafts often have to embark on attitude maneuvers to point their payload at different targets within a specitied time span. This paper analyzes the tracking control problem of spacecraft with three reaction wheels in low earth orbit. The attitude angle, angular velocities and angular acceleration referenced to orbit following coordinates were determined using the kinematics of rigid body. The control law for the reaction wheels was developed based on the spacecraft attitude dynamics. Lyapunov stability theory was used to prove the asymptotic stability of the closed loop control systems. The approach is verified using computer simulation.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2001年第2期102-104,共3页
Journal of Tsinghua University(Science and Technology)
基金
国家自然科学基金资助项目 !(1970 2 0 11)
