High Efficiency Pulsed Plasma Thruster for Satellite Attitude Control and Maneuver
Final rept. 2 Oct 2000-30 Apr 2002
SCIENCE RESEARCH LAB INC SOMERVILLE MA
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The primary objective of this project was to develop Gas-Fed Pulsed Plasma Thrusters GF-PPT that can be used with water vapor or hydrazine as fuel, with vapor pressures of less than 1 Torr necessary to operate the thruster. This propulsion technology can be used to perform orbit phase changes or plane inclination changes for near and intermediate-earth orbit satellites. GF-PPT technology is particularly suited for large DELTA-V, in-plane, orbit phase changes. This technology can therefore complement resistojet technology and allow rapid constellation redeployment to insure prompt satellite coverage of conflicts at any location on the surface of the earth with a constellation of satellites optimized for minimum size and cost. This report discusses GF-PPT thruster performance scaling, as well as hardware and power electronics that were developed in this project.
- Plasma Physics and Magnetohydrodynamics
- Rocket Engines