Evolution of the out-of-plane amplitude for quasi-periodic trajectories in the Earth–Moon system

Pavlak, Thomas A.; Howell, Kathleen C.

doi:10.1016/j.actaastro.2012.07.025

Cited by 26 publications

(9 citation statements)

References 3 publications

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“…Thus, for successful mission operations, th~ system must be modeled as a true fourbody problem, including the Sun's gravity as an important third-body perturbation; accelerations due to lunar eccentricity and solar radiation pressure are incorporated as wei!. The relative effect of these force terms on the evolution of the ARTEMIS P2 trajectory are explored by Pavlak and Howell [6). Operationally, the ARTEMIS mission trajectory design and analysis utilized a full DE421 Moon-Earth-Sun ephemeris model that also incorporated solar radiation pressure acceleration based upon the spacecraft mass and cross-sectional area -in this case, a simplified cannon ball model was used -and a gravity potential model for the Earth with degree and order eight.…”

Section: Environmental Modelingmentioning

confidence: 99%

Earth–Moon libration point orbit stationkeeping: Theory, modeling, and operations

et al. 2014

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Collinear •Earth-Moon libration points have emerged as locations with immediate applications. These libration point orbits are inherently unstable and must be maintained regularly which constrains operations and maneuver locations. Stationkeeping is• challenging due to relatively short time scales for divergence. effects of large orbital eccentricity of the secondary body, and third-body perturbations. Using the Acceleration Reconnection and Turbulence and Electrodynamics of the Moon's Interaction with the Sun (ARTEMIS) mission orbit as a platform, the fundamental behavior of the trajectories is explored using Poincare maps in the circular restricted three-body problem. Operational stationkeeping results obtained using the Optimal Continuation Strategy are presented and compared to orbit stability information generated from mode analysis based in dynamical systems theory.

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Section: Environmental Modelingmentioning

confidence: 99%

Earth–Moon libration point orbit stationkeeping: Theory, modeling, and operations

et al. 2014

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“…These small modifications in models are engineered to highlight the changes resulting from various contributions to the fidelity of the model. This higher-fidelity, four-body ephemeris model is similar to that employed by Pavlak and Howell [25], a Moon-Earth-Sun (MES) point mass model with position histories supplied by JPL DE405 ephemerides. The present model, in contrast to Pavlak and Howell, does not include Solar radiation pressure.…”

Section: A Four-body Ephemeris Modelmentioning

confidence: 98%

Lagrangian coherent structures in various map representations for application to multi-body gravitational regimes

Short

Howell

2014

Acta Astronautica

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“…Therefore, the multiple shooting algorithm is merely a multi-segment corrections process but using the analytical partials computed from propagating segments in the higher-fidelity ephemeris model. Additionally, to represent periodic orbits in such a model, multiple revolutions of the CR3BP periodic orbit are stacked, one on top of the other, and are corrected for position and velocity continuity (Pavlak and Howell, 2012a). The fidelity of the model is enhanced by adding the effects of a large number of celestial bodies as perturbing bodies that depend on the multi-moon system.…”

Section: The Higher-fidelity Ephemeris Modelmentioning

confidence: 99%

Transfer design between neighborhoods of planetary moons in the circular restricted three-body problem

Canales,

Howell,

Fantino

2021

Preprint

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Given the interest in future space missions devoted to the exploration of key moons in the solar system and that may involve libration point orbits, an efficient design strategy for transfers between moons is introduced that leverages the dynamics in these multi-body systems. The moon-to-moon analytical transfer (MMAT) method is introduced, comprised of a general methodology for transfer design between the vicinities of the moons in any given system within the context of the circular restricted three-body problem, useful regardless of the orbital planes in which the moons reside. A simplified model enables analytical constraints to efficiently determine the feasibility of a transfer between two different moons moving in the vicinity of a common planet. In particular, connections between the periodic orbits of such two different moons are achieved. The strategy is applicable for any type of direct transfers that satisfy the analytical constraints. Case studies are presented for the Jovian and Uranian systems. The transition of the transfers into higher-fidelity ephemeris models confirms the validity of the MMAT method as a fast tool to provide possible transfer options between two consecutive moons.

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Evolution of the out-of-plane amplitude for quasi-periodic trajectories in the Earth–Moon system

Cited by 26 publications

References 3 publications

Earth–Moon libration point orbit stationkeeping: Theory, modeling, and operations

Earth–Moon libration point orbit stationkeeping: Theory, modeling, and operations

Lagrangian coherent structures in various map representations for application to multi-body gravitational regimes

Transfer design between neighborhoods of planetary moons in the circular restricted three-body problem

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