Abstract
The three-axis active attitude control method with a momentum wheel and magnetic coils for a pico-satellite is considered. The designed satellite is a 2.5 kg class satellite stabilized to nadir pointing. The momentum wheel performs a pitch-axis momentum bias, nominally spinning at a particular rate. Three magnetic coils are mounted perpendicularly along the body axis for precise attitude control through the switch control mechanism. Momentum wheel start up control, damping control and attitude acquisition control are considered. Simulation results show that the proposed combined control laws for the pico-satellite is reliable and has an appropriate accuracy under different separation conditions. The proposed strategy to start up the wheel after separation from the launch vehicle shows that its pitch momentum wheel can start up successfully to its nominal speed from rest, and the attitude convergence can be completed within several orbits, depending on separation conditions.
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Project supported by the Program for New Century Excellent Talents in University (No. NCET-06-0514), China, and the Postdoctoral Science Foundation of China (Nos. 20081458 and 20080431306)
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Meng, T., Wang, H., Jin, Zh. et al. Attitude stabilization of a pico-satellite by momentum wheel and magnetic coils. J. Zhejiang Univ. Sci. A 10, 1617–1623 (2009). https://doi.org/10.1631/jzus.A0820425
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DOI: https://doi.org/10.1631/jzus.A0820425