Editing Rocket engine (section)

===Electrically powered===
{{Main|Electrically powered spacecraft propulsion}}
{| class="wikitable"
|-
! Type
! Description
! Advantages
! Disadvantages
|-
! [[Resistojet rocket]] (electric heating)
| Energy is imparted to a usually inert fluid serving as reaction mass via [[Joule heating]] of a heating element. May also be used to impart extra energy to a monopropellant.
| Efficient where electrical power is at a lower premium than mass. Higher [[specific impulse|''I''<sub>sp</sub>]] than monopropellant alone, about 40% higher.
| Requires a lot of power, hence typically yields low thrust.
|-
! [[Arcjet rocket]] (chemical burning aided by electrical discharge)
| Identical to resistojet except the heating element is replaced with an electrical arc, eliminating the physical requirements of the heating element.
| 1,600 seconds [[specific impulse|''I''<sub>sp</sub>]]
| Very low thrust and high power, performance is similar to [[ion drive]].
|-
![[Variable specific impulse magnetoplasma rocket]]
| Microwave heated plasma with magnetic throat/nozzle
| Variable ''I''<sub>sp</sub> from 1,000 seconds to 10,000 seconds
| Similar thrust/weight ratio with ion drives (worse), thermal issues, as with ion drives very high power requirements for significant thrust, really needs advanced nuclear reactors, never flown, requires low temperatures for superconductors to work
|-
! [[Pulsed plasma thruster]] (electric arc heating; emits plasma)
| Plasma is used to erode a solid propellant
| High ''I''<sub>sp</sub>, can be pulsed on and off for attitude control
| Low energetic efficiency
|-
! [[Ion thruster|Ion propulsion system]]
| High voltages at ground and plus sides
| Powered by battery
| Low thrust, needs high voltage
|}