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.

Optimal Solar Sail Transfer to Linear Trajectories

QUARTA, ALESSANDRO ANTONIO
Primo
Conceptualization
;
MENGALI, GIOVANNI
Ultimo
Writing – Review & Editing
2013-01-01

Abstract

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.
2013
Quarta, ALESSANDRO ANTONIO; Mengali, Giovanni
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11568/148246
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