As it is impossible to set high accuracy of the initial data for theoretical calculations of the design parameters, such as the mass-centering and inertial characteristics of nanosatellites, the problem of experimental determination of their actual values arises. For a number of reasons, the devices designed for large spacecraft are not appropriate for the small ones. This paper describes a device developed at Samara University for measuring the center of mass coordinates and moments of inertia specifically for CubeSat nanosatellites, as well as a technology for experimental evaluation 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.