An accurate and simple model for flexible satellites for three-dimensional studies

Abstract

In this paper, an accurate and simple model of a satellite with two flexible solar panels for three-dimensional dynamic studies is proposed and compared with other models. In the proposed model, each solar panel is assumed to be rigid and attached to the satellite body via a simple hinge, a torsional spring, and a torsional damper. Kane's method is utilized to derive the equations of motion. The model of flexible satellite with the assumption of Euler-Bernoulli beam for the solar panels, generally used in the literature, has been introduced for comparison. A comprehensive model of flexible satellite, considering solar panels as flexible and finite element panels, has been provided in ADAMS environment as a reference when comparing the two mentioned models. The Euler-Bernoulli model does not appropriately simulate the three-dimensional motion of satellite. Conversely, the hinged, rigid-panel model proposed in this paper provides suitable results in both two-and three-dimensional maneuvers.

Analytical low-jerk reorientation maneuvers for multi-body spacecraft structures

“…Ref. [21] models the behavior of a satellite with two symmetric panels by means of Kane's dynamics, but considering panels as rigid, with flexible hinges.…”