纳卫星变轨段质量矩姿态控制系统设计
收稿日期: 2016-09-12
修回日期: 2016-11-21
网络出版日期: 2016-11-27
基金资助
南京理工大学自主科研专项（30916011101）
Design of moving-mass attitude control system for nanosatellites in orbital transfer stage
Received date: 2016-09-12
Revised date: 2016-11-21
Online published: 2016-11-27
Supported by
The Scientific Research Project of NJUST (30916011101)
陆正亮 , 张翔 , 于永军 , 莫乾坤 , 廖文和 . 纳卫星变轨段质量矩姿态控制系统设计[J]. 航空学报, 2017 , 38(6) : 320778 -320778 . DOI: 10.7527/S1000-6893.2016.0306
A moving-mass control technology is proposed to stabilize the attitude of nanosatellites in orbital transfer stage. After the configuration of actuator masses is obtained, 8 DOF dynamic equations are derived based on momentum and moment of momentum theorem. According to the results of dynamic analysis, a simplified control model is developed. On this basis, a robust controller characterized by a global sliding mode is given to stabilize the yaw and pitch angle and to track the actuator position. The validation of this control system is simulated with the condition of parametric uncertainty. Results indicate that the two-dimensional mass moment control system could rapidly adjust the attitude and have a good robustness against disturbance. It is concluded that this system can be applied for attitude control in orbital transfer.
Key words： orbital transfer; nanosatellite; moving-mass; attitude control; sliding mode control
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