Design and on-orbit performance of the attitude determination and control system for the ZDPS-1A pico-satellite |
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| Institution: | 1. Department of Information Science and Electronic Engineering, Zhejiang University, Hangzhou 310027, China;2. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;1. Keldysh Institute of Applied Mathematics, 125047, Moscow, Miusskaya Sq., 4, Russia;2. Moscow Institute of Physics and Technology, 141701, Dolgoprudny, Institutskiy per. 9, Russia;1. Department of Precision Instrument, Tsinghua University, Beijing 100084, China;2. Space Center, Tsinghua University, Beijing 100084, China |
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| Abstract: | The ZDPS-1A pico-satellite, developed by the Zhejiang University, is featured with a three-axis stabilizing capability. It is 15×15×15 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). |
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