Magnetometer-only linear attitude estimation for bias momentum pico-satellite |
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| Authors: | Ke Han Hao Wang Zhong-he Jin |
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| Institution: | (1) Department of Aeronautics and Astronautics, National Cheng Kung University, Tainan, 70101, Taiwan; |
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| Abstract: | Satellite attitude information is essential for pico-satellite applications requiring light-weight, low-power, and fast-computation
characteristics. The objective of this study is to provide a magnetometer-only attitude estimation method for a low-altitude
Earth orbit, bias momentum pico-satellite. Based on two assumptions, the spacecraft spherical symmetry and damping of body
rates, a linear kinematics model of a bias momentum satellite’s pitch axis is derived, and the linear estimation algorithm
is developed. The algorithm combines the linear Kalman filter (KF) with the classic three-axis attitude determination method
(TRIAD). KF is used to estimate satellite’s pitch axis orientation, while TRIAD is used to obtain information concerning the
satellite’s three-axis attitude. Simulation tests confirmed that the algorithm is suited to the time-varying model errors
resulting from both assumptions. The estimate result keeps tracking satellite attitude motion during all damping, stable,
and free rotating control stages. Compared with nonlinear algorithms, such as extended Kalman filer (EKF) and square root
unscented Kalman filer (SRUKF), the algorithm presented here has an almost equal performance in terms of convergence time
and estimation accuracy, while the consumption of computing resources is much lower. |
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