摘要
为了减少在库仑卫星编队运动过程中不确定因素的影响,避免控制过程中发生抖振现象,提高控制器的稳定性、准确性,设计了适用于二体旋转库仑卫星编队的反馈线性化滑模控制方法。首先在地月系平动点L_2点处附近建立二体旋转库仑卫星编队的动力学模型并进行简化,针对库仑编队动力学特性,在滑模控制中加入了线性化反馈项,保证了编队整体的鲁棒性;仿真结果证明,该方法能够使编队达到预期构型,具有良好的控制性能。
In order to reduce the uncertain factors of coulomb aircrafts formation movement process, avoid chattering of controlling process and increase the stability and veracity of controller, a feedback linearization sliding mode control method applied to the two-satellite formation flying at libration is designed. First the dynamics model two-satellite coulomb formation at earth-moon libration points are established and simplified, the feedback linearization is added with sliding mode control because of the characteristics of dynamics model to ensure robustness of formation. Simulation shows the method can make formation meet desired configuration with favorable control performance.
作者
吴立尧
袁长清
施强
WU Li-yao YUAN Chang-qing SHI Qiang(Aviation University of Air Force, Aircraft and Power Department, Jilin Changchun 130022, China)
出处
《现代防御技术》
北大核心
2017年第1期82-87,共6页
Modern Defence Technology
基金
国家自然科学基金(11372353)
关键词
库仑卫星编队
平动点
反馈线性化
滑模控制
仿真
鲁棒性
Coulomb satellite formation
libration points
feedback linearization
sliding mode control
simulation
robustness
