Attitude control system design and on-orbit performance analysis of nano-satellite鈥斺€淭ian Tuo 1鈥?

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• 作者：Dechao Ran ^{rdcno.11002@163.com" class="auth_mail}Author Vitae ; Tao Sheng ; ^{shengtao-2002@163.com" class="auth_mail}Author Vitae ; Lu Cao ; Xiaoqian Chen ; Yong Zhao
• 关键词：Actuators ; ADCS ; On-orbit performance ; Sensors ; TT-1 nano-satellite
• 刊名：Chinese Journal of Aeronautics
• 出版年：June 2014
• 年：2014
• 卷：27
• 期：3
• 页码：593-601
• 全文大小：2106 K

文摘

“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 commercial-off-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.