plasma environment were carried on in the Magnetoshell magnetic design. In 2022 Freeze, Greason and others published a detailed design for a plasma magnet based sail for a spacecraft named Wind Rider that would use solar wind force to accelerate away from near Earth and decelerate against the magnetosphere of Jupiter in a spaceflight trial mission called Jupiter Observing Velocity Experiment (JOVE). This design employed a pair of superconducting coils each with radius of 9 (m), an alternating current of of 112 (A) with of 4 (Hz). For example, using solar wind parameters =8x10−21 kg/m3 and =500 km/s then =72 km and =4x10−8 T. With =105 m and =2 then . With a coil radius of =1,000 m yields =4x10−4 T from equation . The required RMF power from equation is 13 kW with a required AC coil current =10 A from equation resulting in an induced current of =2 kA from equation . With =5 the plasma magnet force from equation is 197 N. The magnetic force only for the above parameters is 2.8 N from equation and therefore the plasma magnet thrust gain is 71. Using =1 creates very optimistic performance numbers, but since Slough changed this to =2 in 2012, this case is not compared in this article. Plasma magnetoshell (PMS) A 2012 study by Kirtley and Slough investigated the plasma magnet technology for use in the ionosphere of a planet as a braking mechanism in an approach dubbed plasma magnetoshell. The magnetoshell creates drag by ionizing neutral atoms in a planet's ionosphere then magnetically deflecting them. A tether attaching the plasma magnet coils to the spacecraft transfers momentum such that orbital insertion occurs. Analytical models, laboratory demonstrations and mission profiles to Neptune and Mars were described. In 2017 Kelly described using a single-coil magnet with 1/r3 magnetic field falloff rate and more experimental results. In 2019 Kelly and Little published simulation results for magnetoshell performance scaling. A magnet with radius =1 m was tethered to a spacecraft with batteries for 1,000 seconds of operation (longer than aerocapture designs). The simulations assumed a magnet mass =1,000 kg and total magnetoshell system mass of 1,623 kg, suitable for a Cassini–Huygens or Juno size orbiter. The planet's mass and atmosphere atomic composition and density determine a threshold velocity where magnetoshell operation is feasible. Saturn and Neptune have a hydrogen atmosphere and a threshold velocity of approximately 22 km/s. In