Abstract: A tether system for space applications includes at least one electron collector, at least one electron emitter, a power system, and at least one electrodynamic tether electrically coupled to the power system. The electrodynamic tether conducts electrical current between at least one electron collector and at least one electron emitter. Electric current and voltage are measured. Selected tether dynamics and electrodynamics based on the measured electric current and voltage are ascertained. The electric current and/or current distribution is adjusted to thereby control at least one tether system state based on the ascertained selected tether dynamics and electrodynamics.
Abstract: A tether system for space applications includes at least one electron collector, at least one electron emitter, a power system, and at least one electrodynamic tether electrically coupled to the power system. The electrodynamic tether conducts electrical current between at least one electron collector and at least one electron emitter. Electric current and voltage are measured. Selected tether dynamics and electrodynamics based on the measured electric current and voltage are ascertained. The electric current and/or current distribution is adjusted to thereby control at least one tether system state based on the ascertained selected tether dynamics and electrodynamics.