Abstract. The problem of providing aerodynamic stabilization of the nanosatellite is considered in the probabilistic formulation with respect to the angular movement of the nanosatellite after separation from the launch vehicle, in contrast to the known works in which this problem is solved in a deterministic formulation. The formulas for selection of the design parameters (stock, static stability, length, longitudinal moment of inertia) of aerodynamically stabilized nanosatellite are derived. At the low circular orbits the selected values of the parameters provide deviation of the longitudinal axis of the nanosatellite from the center of mass velocity vector less than acceptable with a given probability at the desired height under the given angular velocity errors of the separation system. On the base of numerical calculations, nomograms are created providing a simple and convenient selection of main design parameters values for CubeSat standard nanosatellites.

Keywords: nanosatellite, aerodynamic moment, angle of attack, distribution function, design parameters

References:

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