In this paper, based on previous work on transferring to periodic orbits from Nakamiya et al. [25], Dei Tos et al. [28], and Smet et al. [30], we further extend the periodic orbits and their associated invariant manifolds to orbit capture in the Martian system. Different from the research by Dei Tos et al. [28], we focus on using the periodic orbit to find capture opportunities into Keplerian orbits around Mars, especially the Mars high orbit, which has not been paid attention to before. Instead of capturing the spacecraft directly into the target orbit, the spacecraft transfers first to a stable manifold of a periodic orbit at a low-altitude periapsis and then moves along an unstable manifold of the same periodic orbit to the target orbit. The proposed capture scheme separates a single capture maneuver into several smaller capture maneuvers at different periapsides. Meanwhile, the orbit parameters relative to the target planet are changed by multibody perturbations naturally, which reduces the capture cost. The properties of the manifold-assisted capture are investigated in the rotating frame, and the transfer trajectory in high-fidelity model is designed. The simulation results show that the proposed capture method requires up to 32% less velocity increment than direct capture based on two-body theory. It also has advantages in the flexibility of transfer, extra scientific returns, and less influence on gravity loss, which provides a new option for future planetary exploration missions.

Mars high orbit capture using manifolds in the Sun-Mars system / Li, Xiangyu; Qiao, Dong; Circi, Christian. - In: JOURNAL OF GUIDANCE CONTROL AND DYNAMICS. - ISSN 0731-5090. - 43:7(2020), pp. 1383-1392. [10.2514/1.G004865]

Mars high orbit capture using manifolds in the Sun-Mars system

Christian Circi
2020

Abstract

In this paper, based on previous work on transferring to periodic orbits from Nakamiya et al. [25], Dei Tos et al. [28], and Smet et al. [30], we further extend the periodic orbits and their associated invariant manifolds to orbit capture in the Martian system. Different from the research by Dei Tos et al. [28], we focus on using the periodic orbit to find capture opportunities into Keplerian orbits around Mars, especially the Mars high orbit, which has not been paid attention to before. Instead of capturing the spacecraft directly into the target orbit, the spacecraft transfers first to a stable manifold of a periodic orbit at a low-altitude periapsis and then moves along an unstable manifold of the same periodic orbit to the target orbit. The proposed capture scheme separates a single capture maneuver into several smaller capture maneuvers at different periapsides. Meanwhile, the orbit parameters relative to the target planet are changed by multibody perturbations naturally, which reduces the capture cost. The properties of the manifold-assisted capture are investigated in the rotating frame, and the transfer trajectory in high-fidelity model is designed. The simulation results show that the proposed capture method requires up to 32% less velocity increment than direct capture based on two-body theory. It also has advantages in the flexibility of transfer, extra scientific returns, and less influence on gravity loss, which provides a new option for future planetary exploration missions.
2020
manifolds; mars mission; capture
01 Pubblicazione su rivista::01a Articolo in rivista
Mars high orbit capture using manifolds in the Sun-Mars system / Li, Xiangyu; Qiao, Dong; Circi, Christian. - In: JOURNAL OF GUIDANCE CONTROL AND DYNAMICS. - ISSN 0731-5090. - 43:7(2020), pp. 1383-1392. [10.2514/1.G004865]
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1474891
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