Abstract
Abstract
Magnetically actuated satellite moving on a Sun-synchronous orbit is considered. The satellite maintains one axis attitude towards the Sun while rotating around this direction. Stabilization algorithm utilizes information about the required direction and rotation rate. Evolutionary equations are used to find equilibrium positions and analyze their stability. Conditions on the satellite inertia moments and control parameters are established for different equilibria, including the required motion. Numerical simulation with different disturbing sources is performed to verify stable equilibria existence.
Subject
Space and Planetary Science,Astronomy and Astrophysics,Aerospace Engineering
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