This work focus on controller designing for tethered satellite system (TSS) during orbit maneuvering under transversal thrust. First, dynamic equations of tethered satellite system in orbital maneuvering are given based on dumbbell model. A linear model of the in-plane subsystem is derived for controller designing. Then, an input-to-state stable (ISS) control law for the in-plane angle system is obtained, which will be the reference signal for the tether length subsystem. Next, the tether tension control law based on small-gain theorem guarantees the stability of the closed-loop system and it is proved that states of the system will be forced to a small vicinity of the equilibrium point with properly selected control parameters. Finally, numerical simulation results demonstrate the validity of the proposed algorithm.
An integrated tether rate and tension law during orbital maneuvering via small-gain theorem
01.05.2018
427844 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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