Thrust estimation for HTS-magnet based Magneto Plasma Dynamic Thrusters (MPDT)

Abstract

At present time, electric propulsion is being considered for outer deep space missions. Magneto Plasma Dynamic Thrusters are capable of accelerating semi- neutral plasma gas (Xenon, Iodine, Argon, Ammonia, or Lithium) to a high exhaust velocity using combination of RF power & high magnetic fields. High Temperature Superconducting (HTS) coils can generate high magnetic field due to high operating current density at temperatures below its critical temperature(Tc). These superconducting coils can be cooled by using the cold of outer dark space. The use of 2nd Generation (2G) HTS coils can increase thrust, by increasing high magnetic field with very low power consumption. Thus, specific impulse due to the combination of RF plasma and HTS based superconducting high magnetic field is increased drastically. In this paper, the thrust calculation are carried out for MPDT for varying magnetic fields produced by superconducting coils. The estimation of exhaust velocity and thrust generated by plasma for an MPDT is of great challenge and is required to determine for calculating the life of mission as well as the distance of travel. These estimations are required to support the indigenous development of MPDT.

Investigating the impact of applied magnetic field and current on anode power deposition in AF-MPDT

“…2,3 It boasts a unique set of characteristics, including high specific impulse, remarkable thrust density, versatile propellant options, and scalability. 4,5 As such, the AF-MPDT has long been considered a promising choice for various mission scenarios, particularly those demanding high power. Nevertheless, it has significant drawbacks, such as cathode erosion, 6,7 low efficiency, 8 and demanding ground testing requirements, 9 which rendered these thrusters cost-ineffective until the past decade.…”