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

Abstract

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.

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

“…The computation of FTLE values adds some context for the ARTEMIS maneuver strategy. Previous analysis by Folta et al [5,7], as well as Pavlak and Howell [26], demonstrates that the optimal, plane-constrained stationkeeping maneuvers during the Lyapunov phases of the ARTEMIS trajectory correlate strongly with the stable direction recovered from an approximate monodromy matrix (M) associated with revolutions of the trajectory. The optimal maneuver direction for a stationkeeping cycle aligns with the position projection of the stable eigenvector computed from an approximation to the monodromy matrix.…”

“…Consequently, maneuvers may not always align fully with the "best natural" solution[6] 5. A few of the performed maneuvers during this phase are neglected as not solely stationkeeping maneuvers.…”

Stationkeeping strategy for quasi-periodic orbit around Earth–Moon L2 point

“…l is a slow varying parameter which could be considered as a constant during the trajectory design. 31 Substituting equations (22) and (23) into equation (21), and considering…”

Transfer to a Multi-revolution Elliptic Halo orbit in Earth–Moon Elliptic Restricted Three-Body Problem using stable manifold

“…In the Earth-Moon system, a reference orbit designed in the CRTBP requires frequent (about every 7 days for ARTEMIS) station-keeping maneuvers to offset perturbations introduced by model errors (Breakwell et al, 1974;Folta et al, 2014;Gó mez et al, 1998;Howell and Pernicka, 1993). Energy cost can be reduced if a better nominal orbit in a more realistic model is adopted.…”