Design and on-orbit performance of the attitude determination and control system for the ZDPS-1A pico-satellite

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• 作者：Tian Xiang^a  ; [Author Vitae] ; Tao Meng^b ; ^{mengtao@zju.edu.cn}  ; [Author Vitae] ; Hao Wang^b  ; [Author Vitae] ; Ke Han^a  ; [Author Vitae] ; Zhong-He Jin^b  ; [Author Vitae]
• 关键词：The ZDPS-1A pico-satellite ; Sensors ; Ground simulations ; On-orbit testing ; ADCS
• 刊名：Acta Astronautica
• 出版年：2012
• 出版时间：August-September, 2012
• 年：2012
• 卷：77
• 期：Complete
• 页码：182-196
• 全文大小：2075 K

文摘

The ZDPS-1A pico-satellite, developed by the Zhejiang University, is featured with a three-axis stabilizing capability. It is 15¡Á15¡Á15 cm³ cube-shaped satellite with a total mass of 3.5 kg. ZDPS-1A is the first pico-satellite that has been launched successfully in China. The mission of ZDPS-1A is on-orbit system verification of student-build pico-satellite and wide range earth observation with a micro panoramic camera. A miniature momentum wheel is employed to offer gyro stiffness stability in the pitch (orbit normal) axis. Magnetic coils are employed to generate control torques to achieve the three-axis stabilization of nadir-pointing. The attitude sensors employed in the design include two three-axis magnetometers (TAMs), a three-axis gyro, and two sun sensors. Both ground simulations and on-orbit testing are conducted to verify the feasibility of the given attitude determination and control system (ADCS).