Constrained Motion of Tethered Satellites

Abstract

The orbital motion of tethered satellites is a highly complex nonlinear problem. This investigation formulates a new method that significantly simplifies the dynamic analysis of tethered satellite systems. This is accomplished using the fundamental equation for constrained dynamic systems, which was formulated by Udwadia and Kalaba. As a result of this new method, a study of the periodicity of tethered satellite motion is conducted and an extension to formation flying satellites is made. With varying fixed tether lengths, the system motion seems to transition from periodic to quasi-periodic. The simplified method is also applied to the computation of the control force required for formation flight.