Electrodynamic Tether at Jupiter-I: Capture Operation and Constraints

Tethered spacecraft missions to the Jovian system suit the use of electrodynamic tethers because: 1) magnetic stresses are 100 times greater than at the Earth; 2) the stationary orbit is one-third the relative distance for Earth; and 3) moon to is a nearby giant plasma source. The (bare) tether is a reinforced aluminum foil with tens of kilometer length L and a fraction of millimeter thickness h, which collects electrons as an efficient Langmuir probe and can tap Jupiter's rotational energy for both propulsion and power. In this paper, the critical capture operation is explicitly formulated in terms of orbit geometry and established magnetic and thermal plasma models. The design parameters L and h and capture perijove radius r(p) face opposite criteria independent of tape width. Efficient capture requires a low r(p) and a high L(3/2)/h ratio. However, combined bounds on tether bowing and tether tensile stress, arising from a spin made necessary by the low Jovian gravity gradient, require a high r(p) and a low L(5/2)/h ratio. Bounds on tether temperature again require a high r(p) and a low L(3/8)/(tether emissivity)(1/4) ratio. Optimal design values are discussed.