There is an increased requirement for microsatellites to support such future missions as formation-flying space-based surveillance, space control, and on-orbit satellite servicing. Devices that can provide precise impulse bits in the 10-micro newton range may be enabling for a new fleet of 25-kg class spacecraft supporting these missions. in response to this need the Air Force Research Laboratory is developing a miniaturized propulsion unit: the Micro- Pulsed Plasma Thruster (Micro-PPT). Like a standard PPT, the Micro-PPT uses a surface discharge across the face of a solid Teflon(TM) propellant to create and accelerate a combination of plasma and neutral vapor. The Micro-PPT substantially differs from the standard design by using a self-igniting discharge and eliminating the separate igniter circuit from the thruster. This simplification enables the order-of-magnitude reductions in the thruster size and operational power level required to meet microsatellite propulsion requirements.
Micropropulsion Research at AFRL
2000
13 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Electric & Ion Propulsion , Unmanned Spacecraft , Propulsion systems , Artificial satellites , Thrusters , Requirements , Power levels , Orbits , Air force research , Neutral , Vapors , Plasmas(Physics) , Reduction , Surfaces , Pulses , Precision , Laboratories , Air force facilities , Circuits , Miniaturization , Igniters , Space maintenance , Micro-ppt(Micro-pulsed plasma thruster)
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