a Neptune mission a =6 km is required for a 5,000 kg spacecraft and must average 50 kN for the maneuver duration. The model overestimates performance for N2 (Earth, Titan) and CO2 (Venus, Mars) atmospheres since multiple ion species are created and more complex interactions occur. Furthermore, the relatively lower mass of Venus and Mars reduces the threshold velocity below that of feasible magnetoshell operation. The paper states that aerocapture technologies are mature enough for these mission profiles. In 2021 Kelly and Little published further details for use of drag-modulated plasma aerocapture (DMPA) that when compared to Adaptable Deployable Entry and Placement Technology (ADEPT) for drag-modulated aerocapture (DMA) to Neptune that could deliver 70% higher orbiter mass and experience 30% lower stagnation heating. Beam powered magsail (BPM) A beam-powered of M2P2 variant, MagBeam was proposed in 2011. In this design a magnetic sail is used with beam-powered propulsion, by using a high-power particle accelerator to fire a beam of charged particles at the spacecraft. The magsail would deflect this beam, transferring momentum to the vehicle, that could provide higher acceleration than a solar sail driven by a laser, but a charged particle beam would disperse in a shorter distance than a laser due to the electrostatic repulsion of its component particles. This dispersion problem could potentially be resolved by accelerating a stream of sails which then in turn transfer their momentum to a magsail vehicle, as proposed by Jordin Kare. Performance comparison The table below compares performance measures for the magnetic sail designs with the following parameters for the solar wind (sw) at 1 AU: velocity = 500 km/s, number density = 5x106 (m−3), ion mass = 1.67x10−27 kg a proton mass, resulting in mass density = 8.4x10−21 (kg/m3), and coefficient of drag =5 where applicable. Equation gives the magnetic field at magnetopause as ≈ 36 nT, equation gives the ion gyroradius ≈ 72 km for =2. Table entries in boldface are from a cited source as described in the following: Equation determines force for the Magsail (MS) divided by the Freeland correction factor 3.1, equation defines the force for the plasma magnet (PM) with the assumed magnetic field falloff rate =2. The force for the magnetic sail alone is from equation . Thrust gain for the magneto plasma sail (MPS) is the simulation and/or experimentally determined value with force defined equation to account for thrust loss due to operation