The amount of available propellant limits low-Earth orbit satellite lifetime due to the necessity of drag makeup. An electric propulsion device that uses in situ ions as propellants is considered as an alternative method for satellite drag makeup. This work presents a tool that consists of a one-dimensional thruster mathematical model integrated with the NASA International Reference Ionosphere to provide ion and neutral species densities for an electrostatic electric propulsion approach. This mathematical model predicts thrust, drag, and thruster power. The thrust-to-drag ratio and thruster power are averaged over the entire mission duration of one year and compared with various circular orbits and satellite configurations: 300–1000 km orbit altitude, 0–60 deg orbit inclination, low to high solar activity, 0.1 5.0 m 2 satellite frontal area, 1–10 kV acceleration voltage, and 1 10 m 2 total grid area. The Satellite Tool Kit provides orbit propagation. An average thrust-to-drag ratio greater than one is achievable for many thruster and orbit configurations considered in this analysis, at power levels less than 90 W. Most satellite missions at altitudes of less than 400 km may fall into the region in which the thrust-to-drag ratio is less than one. Thrust-to-drag ratio values of less than one will still benefit satellites by extending mission lifetimes for months or years with average power requirements less than 100 W.


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    Title :

    Atmospheric Electric Propulsion Mission Performance Tool


    Contributors:

    Published in:

    Publication date :

    2014-05-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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