کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1764447 | 1020056 | 2013 | 12 صفحه PDF | دانلود رایگان |
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.
► 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.
Journal: Advances in Space Research - Volume 51, Issue 3, 1 February 2013, Pages 411–422