This paper addresses the heliocentric in-orbit repositioning problem of an E-sail-based spacecraft that covers a circular parking orbit, with the assumption that the propulsive acceleration is directed along the Sun-spacecraft line. The analysis exploits the possibility of reducing the problem to the dynamics of an equivalent nonlinear oscillator with a single degree of freedom. The analytical expression of the spacecraft heliocentric trajectory, which is available in polar form when the motion is periodic, is used to obtain approximate relationships between the E-sail performance, the flight time and the phasing angle. The approximate analytical model is validated through numerical simulations, and the last part of the paper discusses a comparison with the optimal in-orbit repositioning transfers available in the recent literature.

Electric sail phasing maneuvers with radial thrust

Bassetto M
Primo
Conceptualization
;
Boni L
Secondo
Validation
;
Mengali G
Penultimo
Writing – Original Draft Preparation
;
Quarta A
Ultimo
Methodology
2019-01-01

Abstract

This paper addresses the heliocentric in-orbit repositioning problem of an E-sail-based spacecraft that covers a circular parking orbit, with the assumption that the propulsive acceleration is directed along the Sun-spacecraft line. The analysis exploits the possibility of reducing the problem to the dynamics of an equivalent nonlinear oscillator with a single degree of freedom. The analytical expression of the spacecraft heliocentric trajectory, which is available in polar form when the motion is periodic, is used to obtain approximate relationships between the E-sail performance, the flight time and the phasing angle. The approximate analytical model is validated through numerical simulations, and the last part of the paper discusses a comparison with the optimal in-orbit repositioning transfers available in the recent literature.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11568/991150
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