NASA NTRS · 20090028726
Electrodynamic Tethers for Spacecraft Propulsion
Abstract
Electrodynamic (Drag) Tether Thrust Principles: a) Uses both solar energy and consumes no propellant. b) Tether's orbital velocity v (approx. 7500 m/s) through North-pointing geomagnetic field B(sub north) (0.18 - 0.32 Gauss) induces voltage (35 - 160 V/km) in tether. c) Return current is through surrounding plasma. d) Current I produces a drag thrust force F on the tether. e) Magnetic force F from current I through insulated tether of length l: F = lI x B(sub north).
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Johnson, Les. 2009-02-01. Electrodynamic Tethers for Spacecraft Propulsion. https://ntrs.nasa.gov/citations/20090028726
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