| Attitude control system design and on-orbit performance analysis of nano-satellite––‘‘Tian Tuo 1’’ |
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| 作者姓名： | Ran Dechao Sheng Tao Cao Lu Chen Xiaoqian Zhao Yong |
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| 作者单位： | College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410072, China |
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| 基金项目： | The authors thank all the teachers, researchers, engineers and students involved in satellite design for the great effort placed for the success of the TT-1 nano-satellite mission. The authors also thank the reviewers for the useful comments which greatly improve the paper. |
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| 摘 要： | ‘‘Tian Tuo 1'(TT-1) nano-satellite is the first single-board nano-satellite that was successfully launched in China. The main objective of TT-1 is technology demonstration and scientific measurements. The satellite carries out the significant exploration of single-board architecture feasibility validation, and it is tailored to the low-cost philosophy by adopting numerous commercialoff-the-shelf(COTS) components. The satellite is featured with three-axis stabilization control capability. A pitch bias momentum wheel and three magnetic coils are adopted as control actuators.The sun sensors, magnetometers and a three-axis gyro are employed as the measurement sensors.The quaternion estimator(QUEST) and unscented Kalman filter(UKF) method are adopted for the nano-satellite attitude determination. On-orbit data received by ground station is conducted to analysis the performance of attitude determination and control system(ADCS). The results show that the design of ADCS for TT-1 is suitable, robust and feasible.
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| 关 键 词： | 控制系统设计 卫星姿态确定 纳米卫星 性能分析 无迹卡尔曼滤波 测量传感器 ADCS 太阳传感器 |
| 收稿时间： | 2013-05-09 |
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