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.


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    Micropropulsion research at AFRL

    Gulczinski III, Frank / Dulligan, Michael / Lake, James et al. | AIAA | 2000


    Micropropulsion Research at AFRL (Postprint)

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    Lewis, D. / Janson, S. / Cohen, R. et al. | British Library Conference Proceedings | 1999