Abstract
The dynamic simulation of satellite components requires the ten inertia parameters (mass, mass center three coordinates and inertia tensor, 3×3 matrix). The aim of the present work is the design and the realization of a testing machine able to determine all these parameters for small components (assumed to have a rigid body behavior), with particular attention to space scientific experiments. The authors, by an analysis of the state of the art and by an analytical classical approach, have determined a measuring methodology which doesn't currently find application in industry. A testing machine was designed and realized to implement the abovementioned methodology. Its structural integrity and dynamic behavior were investigated by finite element modeling and analysis (FEA) and multi body modeling and simulation (MBS). The machine functionality and precision were tested by a first test campaign conducted on a simple device.
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