Highlights ► A mission toward circumsolar space may be accomplished using a SEP spacecraft. ► This choice is encouraged by the high Delta V required by a bi-impulsive transfer. ► The simulation results are collected into graphs and tables for a trade- off analysis.
Abstract The aim of this paper is to explore the capabilities of a solar electric propelled spacecraft on a mission towards circumsolar space. Using an indirect approach, the paper investigates minimum time of transfer (direct) trajectories from an initial heliocentric parking orbit to a desired final heliocentric target orbit, with a low perihelion radius and a high orbital inclination. The simulation results are then collected into graphs and tables for a trade-off analysis of the main mission parameters. Finally, a comparison of the performance between a solar electric and a (photonic) solar sail based spacecraft is discussed.
Time-optimal trajectories to circumsolar space using solar electric propulsion
Advances in Space Research ; 51 , 3 ; 411-422
2012-09-12
12 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Time-optimal trajectories to circumsolar space using solar electric propulsion
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