NirViaje
commented
5 years ago 
Metal Propellants Thruster
- Preliminary Thrust Stand Measurements of an Ablative Gallium Electromagnetic (GEM) Thruster, Dr. Robert E. Thomas, Thomas Haag, NASA Glenn Research Center, 2012
- Design and Performance Estimates of an Ablative Gallium Electromagnetic Thruster, Robert E. Thomas, 2012
- https://wikipedia.org/wiki/Magnetoplasmadynamic_thruster
- Investigation of a Gallium MPD Thruster with an Ablating Cathode, Robert E. Thomas, Rodney L. Burton, et al., 2009, NASA-Marshall Space Flight Center
- Self-Applied Magnetic Field Effects on Solid Propellant MPD Thruster Performance, Italy, 1999
- Enthalpy of vaporization: Iron 3134 K 6090J/g, Water 2257J/g, Gallium 258.7 kJ/mol, Li 145.92kJ/mol
- https://space.stackexchange.com/questions/2561/what-are-the-main-problems-with-magneto-plasma-dynamic-mpd-thrusters
Li LFA
The lithium Lorentz-force accelerator (Li-LFA) uses a multichannel hollow cathode and lithium propellant to substantially reduce the cathode erosion problem while significantly raising the thrust efficiency at moderately high power levels. For example, a 200-kW Li-LFA has demonstrated essentially erosion-free operation over 500 hr of steady thrusting at 12.5 N, 4000 sec Isp, and 48% efficiency. Since no other electric thruster has yet shown such a high power processing capability, the Li-LFA is at the forefront of propulsion options for nuclear-powered deep-space exploration and heavy cargo missions to the outer planets.
- Lorentz Force Accelerator with an Open-ended Lithium Heat Pipe, E.Y. Choueiri et al., EPPDyL Princeton University
- Thrust Scaling in Applied-Field Magnetoplasmadynamic Thrusters, William J. Coogan, Dissertation, Princeton University
- Electric Propulsion and Plasma Dynamics Laboratory, Princeton University
- Video | Mars Mission Using Near-Term Plasma Propulsion, Will Coogan, EPPDyL
Drawback (suggested by ncc21382
- Cathode may not sustainable under the crucially high temperature
PIT
Pulsed Inductive Thruster (suggested by ncc21382
Advantages
- Unlike an electrostatic ion thruster which uses an electric field to accelerate only one species (positive ions), a PIT uses the Lorentz body force acting upon all charged particles within a quasi-neutral plasma.
- Unlike most other ion and plasma thrusters, it also requires no electrodes (which are susceptible to erosion)
- and its power can be scaled up simply by increasing the number of pulses per second. A 1-megawatt system would pulse 200 times per second.
- Pulsed inductive thrusters can maintain constant specific impulse and thrust efficiency over a wide range of input power levels by adjusting the pulse rate to maintain a constant discharge energy per pulse. It has demonstrated efficiency greater than 50%.[2]
- PITs can use a wide range of gases as a propellant, such as water, hydrazine, ammonia, argon, xenon…
Due to this ability, it has been suggested to use PITs for Martian missions: an orbiter could refuel by scooping CO2 from the atmosphere of Mars, compressing the gas and liquefying it into storage tanks for the return journey or another interplanetary mission, whilst orbiting the planet.[3]
Drawback
- the valve might failure during high duty of shift on and off, cascade compensation might be in need
Electric
电磁
静电
机械