کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1715165 | 1013356 | 2013 | 8 صفحه PDF | دانلود رایگان |
![عکس صفحه اول مقاله: Optimal solar sail transfer to linear trajectories Optimal solar sail transfer to linear trajectories](/preview/png/1715165.png)
The aim of this paper is to characterize a mission toward a heliocentric linear trajectory (that is, a rectilinear orbit) and to investigate the performance of a solar-sail-based spacecraft to accomplish the transfer phase using an ideal or an optical force model. A similar problem has been recently discussed under simplified assumptions, but new results are now provided with a thorough analysis that uses a three dimensional transfer orbit or a piecewise constant steering law. The paper investigates a complex mission scenario, where the solar sail returns back to Earth after a scientific probe is released along a target linear trajectory.
► A mission toward a rectilinear orbit may be accomplished using a solar-sail.
► This choice is encouraged by the high Delta V required by a bi-impulsive transfer.
► An orbit with aphelion radius of 5.2 AU requires an acceleration of 3.5 mm/s2.
► The mission can be completed with a flight time of less than 3 years.
Journal: Acta Astronautica - Volume 82, Issue 2, February 2013, Pages 189–196