The Selection of the Design Parameters of the Aerodynamically Stabilized Nanosatellite of the CubeSat Standard

The problem of selecting the design parameters of aerodynamically stabilized nanosatellite of the CubeSat standard is considered. The formulas for selecting the design parameters (static stability factor, length, longitudinal moment of inertia) of the aerodynamically stabilized nanosatellite of the CubeSat standard are obtained. At the low circular orbits the design parameters provides deviation of the longitudinal axis of the nanosatellite from the center of mass velocity vector that is less than acceptable with a given probability on a given height at the known errors of angular velocity for separation system.