An Improved Dynamic Friction Rejection Attitude Stability Control Strategy  

作　　者：Yonghai Wang Gang Meng Jianlin Li Yongtao Shui Baogang Lu 

机构地区：[1]Beijing Institute of Space Long March Vehicle, China Academy of Launch Vehicle Technology

出　　处：《Journal of Harbin Institute of Technology(New Series)》2019年第5期79-87,共9页哈尔滨工业大学学报（英文版）

摘　　要：The attitude stability control of under actuated spacecraft that used two reaction wheels in the presence of dynamic friction disturbance is handled. A novel improved control approach with a combination of a singular control law based on quaternion and extended state observer (ESO) is employed to establish a stabilization control so as to restrain the effect of friction. The corresponding simulation results demonstrate the highly stable accuracy and performance compensated dynamic friction. Furthermore if there is a non zero initial condition in under actuated axis the attitude stability can be enhanced with a magnetic torquer. Simulations for a nano spacecraft denote a potential application value in pointing accuracy using two reaction wheels and a magnetic torquer.The attitude stability control of under-actuated spacecraft that used two reaction wheels in the presence of dynamic friction disturbance is handled. A novel improved control approach with a combination of a singular control law based on quaternion and extended state observer(ESO) is employed to establish a stabilization control so as to restrain the effect of friction. The corresponding simulation results demonstrate the highly stable accuracy and performance compensated dynamic friction. Furthermore, if there is a non-zero initial condition in under-actuated axis, the attitude stability can be enhanced with a magnetic torquer. Simulations for a nano-spacecraft denote a potential application value in pointing accuracy using two reaction wheels and a magnetic torquer.

关 键 词：nanospacecraft dynamic FRICTION SINGULAR control linear EXTENDED state OBSERVER magnetic torquer 

分 类 号：TP273.2[自动化与计算机技术—检测技术与自动化装置]