A class of miniaturized pulsed plasma thrusters (PPT), known as MicroPPTs, is currently in development at the Air Force Research Laboratory. The MicroPPTs use a surface discharge across solid Teflon(TM) propellant to provide precise impulse bits in the 10 microN-s range. In the near term, these thrusters can provide propulsive attitude control on 150-kg-class spacecraft using 1/5th the dry mass of conventional torque rods and reaction wheels. Eventually these thrusters are designed for primary and attitude control propulsion on future 25- kg class spacecraft envisioned for such missions as formation flying sparse aperture arrays for space-based surveillance, on-orbit satellite servicing, and space control. A synopsis of the status of the thruster is presented, discussing development, lifetime, performance, and environmental testing.
AFRL MicroPPT Development for Small Spacecraft Propulsion
2002
16 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Astronautics , Propulsion systems , Thrusters , Space propulsion , Plasma engines , Spacecraft , Attitude control systems , Space surveillance , Electrodes , Environmental tests , Torque , Miniaturization , Electric propulsion , Space maintenance , Reaction control systems , Solid propellants , Space based , Microppt , Ppt(Pulsed plasma thrusters) , Dry mass , Reaction wheels , On orbit servicing , Teflon(Tm)
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