Estimate of angular velocity of CubeSat nanosatellite separation from orbital deployer

CubeSat nanosatellites (NS) continue to acquire popularity. Most commonly, they are launched using orbital deployers, which act as an interface between the NS and the launch vehicle. When getting out of the orbital deployer, a nanosatellite acquires angular velocity relative to its center of inertia. Since it is important to maintain a specific space orientation of a nanosatellite for a number of objectives, a need arises to estimate the separation angular velocity. In this paper we preset a mathematical model of the separation process of CubeSat nanosatellites from P-POD-type orbital deploy er. Statistical modeling is also performed with regard to measurement errors of the nanosatellite parameters and its random location inside the orbital deployer. As an example, the SamSat-ION nanosatellite developed at Samara University is considered. The mathematical model obtained in this work may be useful for nanosatellite developers for estimating the separation angular velocity of a nanosatellite.