Dynamic and vibration analysis of a satellite with flexible panels equipped with variable-speed control moment gyros

Abstract

The model of a satellite equipped with N single-gimbal variable-speed control moment gyros (VSCMGs) and two symmetric flexible solar panels is introduced, and the equations of motion have been derived using Kane's method. The aim is to develop a dynamic model with sufficiently reliable and accurate information. The number of VSCMGs, their positions, and the direction of gimbals axis are assumed arbitrary. Further, no assumption has been made regarding ignoring mass and inertia of the gimbals. Each solar panel has been assumed to be rigid and attached to the satellite body by a simple hinge equipped with a torsional spring and a damper. Analytical solutions have been derived and implemented in MATLAB software for a pyramid configuration of VSCMGs and have been compared with the results obtained from an ADAMS model to verify the results. Simulation results show good agreement between the analytical approaches and the numerical simulations. The aforementioned hinged rigid panel model is also compared with the Euler—Bernoulli models in the literature. It has been shown that the proposed model with hinged rigid panels provides appropriate results in both two- and three-dimensional motions. In contrast, the Euler—Bernoulli beam model can provide reliable results merely in particular manoeuvres, owing to missing of the gyroscopic effect of the panels in three-dimensional motions.