Electric propulsion concepts are compared on the basis of trip time for the low earth orbit (LEO) to geosynchronous earth orbit (GEO) mission. Resistojet, arcjet, magnetoplasmadynamic (MPD), pulsed inductive, and ion engine thruster concepts are included. The optimum (minimum trip time) value of specific impulse is found to be dependent upon the specific mission and system being considered. As expected, the devices which can deliver good efficiency at low specific impulses promise the fastest trip times. The solution for trip time and propellant mass for the constant power, continuous low acceleration orbit transfer problem (one way and round trip) is presented in nomograph form. The influences of mission Delta V, thruster efficiency, specific impulse, power, power and propulsion system mass, and payload mass are clearly illustrated.


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    Title :

    A comparison of potential electric propulsion systems for orbit transfer


    Contributors:

    Conference:

    Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference ; 1982 ; New Orleans, LA


    Publication date :

    1982-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :