Electrodynamic tethers have been proposed for satellite propulsion in the magnetic fields of Earth and the Gas Giant planets.

Is it realistic to consider using the Sun's magnetic field for electrodynamic propulsion in the inner solar system? The Sun's magnetic field is stronger than Jupiter’s, and the solar wind is electrically conductive https://en.wikipedia.org/wiki/Interplanetary_magnetic_field so the two primary requirements for electromagnetic tether propulsion are met.

Magnetic field strength increase closer to the Sun. The interplanetary magnetic field strength is much too low at 1AU (almost an order of magnitude less than Earth LEO). But the solar field strength at the Sun's poles is more than an order of magnitude greater than Earth's. At some distance inside 1AU, the interplanetary magnetic field strength must be equal to or greater than Earth's.

At what orbital radius is electrodynamic tether propulsion realistic? A solar powered, tether-propelled spacecraft could potentially perform long term, propellant-free missions in this zone.


2 Answers 2


Some figures I found suggest that 300km above the earth would have a strength around 0.24 gauss (Research India), while the interplanetary field at 1AU is only about 50 micro gauss (Valee). I suspect that it would be very difficult to make use of a field that weak.

  • 1
    $\begingroup$ Valee also says "The large scale solar magnetic field near the poles of the Sun ... <has> a strength of about 10 Gauss." Presumably the field strength varies quite a bit in the inner solar system. Both solar power intensity and field strength increase as heliocentric orbital radius decreases. At what orbital radius is electrodynamic tether propulsion realistic? $\endgroup$
    – Woody
    May 5 at 22:37
  • $\begingroup$ I've added links to a few related questions. I'm not sure but, some answers might have info/links worth citing here as well. $\endgroup$
    – uhoh
    May 6 at 0:40

There’s no definition of “practical” except in some context.

Mission proposals exist using IMF tethers, given the parameters of 1) long-enough tethers, of good enough properties, and 2) light-enough spacecraft, reducing the demand on the forces needed. In turn, 2) implies mission schedules work out, which itself implies trajectory design works out to something usable.

The specific proposal I saw was for a fleet of ~3U cubesats, each taking X years to reach a target using a tether of Y length. Given the mass of a 3U, and X, (and of course the observed field strength,) length Y was certainly long, but no longer than a hundred other proposed tethers. All told, the proposal was no wackier than a hundred other tether-based concepts.

Change the parameters to a human capsule, going a significant distance, within however many days to weeks, and the proposal goes wacky. The tether length necessary will exceed any human construct.


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