Pulsed plasma thrusters (PPT's) offer the combined benefits of extremely low average electric power requirements (1 to 150 W), high specific impulse (approximately 1000 s), and system simplicity derived from the use of an inert solid propellant. Potential applications range from orbit insertion and maintenance of small satellites to attitude control for large geostationary communications satellites. While PPT's have been used operationally on several spacecraft, there has been no new PPT technology development since the early 1970's. As result of the rapid growth in the small satellite community and the broad range of PPT applications, NASA has initiated a development program with the objective of dramatically reducing the PPT dry mass, increasing PPT performance, and demonstrating a flight ready system by October 1997. This paper presents the results of a series of near-Earth mission studies including both primary and auxiliary propulsion and attitude control functions and reviews the status of NASA's on-going development program.
Pulsed Plasma Thruster Technology for Small Satellite Missions
1995
14 pages
Report
No indication
English
Unmanned Spacecraft , Attitude control , Auxiliary propulsion , Communication satellites , Plasma engines , Plasma propulsion , Small scientific satellites , Spacecraft maneuvers , Technology assessment , Technology utilization , Geosynchronous orbits , Orbit insertion , Solid propellants , Specific impulse , Synchronous platforms
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