The state-of-the-art performance of nine electric propulsion devices in terms of specific impulse and thruster and power processor efficiency and specific mass are discussed. Initial vehicle mass and strip time for four cases, Delta V of 1 and 6 km/s and payload mass of 3000 and 30,000 kg, were calculated and compared to a state-of-the-art storable chemical propulsion system. Situations where electric propulsion systems give a lower initial vehicle mass than a chemical propulsion system are shown. The advantages of the beamed energy thrusters, the microwave and laser thrusters, which do not carry their power source with them are also shown. The desirability of having a low power supply specific mass for those electric propulsion systems which must carry their power supply with them is demonstrated.
Survey of Electric Propulsion Thruster Applicability to Near Earth Space Missions
1988
9 pages
Report
No indication
English
Electric propulsion for near-Earth space missions
NTRS | 1980
|Electric Propulsion for Near-Earth Space Missions
NTIS | 1980
|