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We consider the problem of controlled reduction of angular acceleration of a re-entry spacecraft with a small mass and aerodynamic asymmetry. An analytical dependence is proposed to control the angular acceleration of the spacecraft, providing a reduction in the aerodynamic asymmetry.
In this study, we model a collision of a nanosatellite with space debris or micrometeoroids, leading to rotational motion of a nanosatellite. We consider the problem of controlled reduction of acquired angular velocity of a nanosatellite. The control process is based on the use of three electromagnets.
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