Empirical Definition of the Behavior of a Novel Damper for Small Spacecraft with Flexible Appendages

摘要

As small satellites become increasingly capable, opportunities now exist for them to perform complicated functions including missions beyond Earth orbit. For power, these missions may require large, flexible solar arrays that would produce dynamic loads. This article presents research into the feasibility of a magnetorheological fluid (MRF) damper for flexible appendages on a small satellite application. Preliminary modeling of the proposed damper has been performed with a numerical MATLAB™ simulation, however that simulation makes the significant simplifying assumption of proportional damping. This article presents research to replace that assumption with empirically derived values that vary as a function of electrical current flow. The goal is to improve the numerical model to include empirically-derived values for yield strength and damping ratio. Later research will then use the model to implement a control algorithm to optimize damping performance.