Abstract
This paper studies the dynamics of the angular motion of CubeSat nanosatellites with the passive stabilization systems of different types: aerodynamic, aerodynamic-gravitational, gravitational, gravitational-aerodynamic systems. The research was carried out in a probabilistic formulation. Using the obtained analytical distribution functions of the maximum angle of the nanosatellite longitudinal axis deviation from the required direction (orbital velocity vector, or local vertical), the formulas for selecting design parameters (geometrical dimensions, static stability margin, inertia moments) are derived. In the circular orbit at the required flight altitude, these parameters provide the deviation of the longitudinal axis from the required direction less than the allowable value with a given probability for a specified error of the initial angular velocity formed by the separation system. The nomograms for selecting the main design parameters of a CubeSat nanosatellite have been constructed.
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