This paper describes a metal plasma thruster (MPT) that is suited to nano- and microsatellites. The MPT uses solid metal propellant (hence requires no liquids, gases, flow valves, or flow controls), has no moving parts, generates approximately 5000    N · s / U , and may be packaged into ½ - U , 1-U, and multiple-U increments. A vacuum arc generates a metal plasma plume that accelerates into space at 6.8    km / s (platinum, Pt) to 30.6    km / s (magnesium, Mg) to generate thrust ( 10    μ N / W ). The range of specific impulse is from 693 s (Pt) up to 3119 s (Mg). Spacecraft interface is simple: the autonomous MPT requires only a DC input (7–28 V) and a start/stop control pulse from the satellite. The MPT is simpler and more rugged than ion engines and Hall thrusters, which are not easily scaled down in mass and power for < 100    kg satellites, and provides superior total impulse per kilogram. The MPT is easier to operate than equivalent-sized alternatives: field emission electric propulsion thruster, xenon gas radiofrequency thruster, and pulsed plasma thruster.


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    Titel :

    Metal Plasma Thruster for Small Satellites


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.07.2020




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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