Abstract
Due to inability to set a high accuracy of initial data in theoretical calculations of mass-centering and inertial characteristics of nanosatellites, a problem arises concerning the experimental determination of their actual values. For a number of reasons, the devices designed for large spacecraft are not appropriate for small ones. This paper describes a device for measuring the center of mass coordinates and moments of inertia developed at Samara University specifically for CubeSat nanosatellites, as well as a technology for experimental determination of the design parameters of nanoclass spacecraft. The accuracy of determining the design parameters using the proposed device is confirmed by a series of experiments with standards. Key words: nanosatellite, center of mass coordinates, moment of inertia, inertia tensor, measuring platform.
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