A new method has been developed for obtaining approximate near-optimal low-thrust interplanetary transfers using solar electric propulsion spacecraft. The trajectory-calculation method consists of analytic curve-fit functions that have been empirically derived from a database of minimum-propellant coplanar transfers between Earth's orbit and circular target orbits. It is assumed that the transfer begins with a powered arc, followed by a single coast arc, and ends with a second powered arc. The curve-fit functions depend on the mean thrust acceleration and target radius. A scaling technique transforms the Earth-orbit-based solutions in order to provide outward and inward trajectories between circular orbits of arbitrary radius. The inputs to the trajectory tool are the initial and final circular radii, initial spacecraft mass, input power, specific impulse, and thruster efficiency; and the computed (output) values are trip time, transfer angle, coast arc angle, and ΔV. The curve-fitting method is extremely fast, with run times of a few milliseconds. Numerical trials show that the curve-fitting technique accurately predicts trip time, with the largest errors ranging from 2 to 4%. Velocity increment or ΔV errors (and hence delivered-mass errors) are negligible. Finally, because the curve-fitting method can predict transfer angle, the trajectory tool can estimate departure and arrival dates. This curve-fitting method provides very rapid low-thrust interplanetary trajectory analysis and is therefore well suited as a preliminary mission design tool.


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    Titel :

    Efficient Computation of Optimal Interplanetary Trajectories Using Solar Electric Propulsion


    Beteiligte:


    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.54 Flugführung
    Lokalklassifikation TIB:    770/7040