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Electromagnetic Stabilization System Algorithm During Energy Restriction Mode for the Near-Symmetric Satellites


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DOI: https://doi.org/10.15866/irease.v15i1.20429

Abstract


The electromagnetic system of Attitude Determination and Control System (ADCS) is widely used on spacecraft for the Earth Remote Sensing Spacecraft (RSS). Main purposes of ADCS are momentum desaturation of Reaction Wheels (RW), detumbling the initial angular velocity after deployment and the Sun acquisition. 3-dof control that uses magnetorquer rods (MTR) in a standard placement (each MTR is along the main axis of inertia) needs simultaneous work of each MTR. Orientation issues arise frequently when energy is limited, which does not allow turning on several MTRs simultaneously. An algorithm for 3-dof MTR stabilization is proposed. Spacecraft in a low near-circular orbit uses only one MTR at a time due to the method of mobile control with intelligent channel switching. Near-circular spacecraft orbit flight simulation with inclination from 30° up to 90° showed the possibility to use this method during 3-dof stabilization. The reorientation process results, energy gain using two electromagnetic control units and the energy consumption with the required stabilization accuracy were shown.
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Keywords


Electromagnetic Attitude Determination and Control System; Sequential Control Algorithm During Energy Restriction Mode; 3-dof Spacecraft Stabilization; Energy Saving Mode

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References


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