scholarly journals A Modified Targeting Strategy for Station-Keeping of Libration Point Orbits in the Real Earth-Moon System

2019 ◽  
Vol 2019 ◽  
pp. 1-11
Author(s):  
Yang Jin ◽  
Bo Xu
Keyword(s):  
State Transition ◽  
Libration Point ◽  
Three Body Problem ◽  
Station Keeping ◽  
Moon System ◽  
The Real ◽  
Libration Point Orbits ◽  
Triangular Libration Points ◽  
Three Body ◽  
Targeting Strategy

In this paper, a modified targeting strategy is developed for missions on libration point orbits (LPOs) in the real Earth-Moon system. In order to simulate a station-keeping procedure in a dynamic model as realistic as possible, LPOs generated in the circular restricted three-body problem (CRTBP) are discretized and reconverged in a geocentric inertial system for later simulations. After that, based on the dynamic property of the state transition matrix, a modified strategy of selecting target points for station-keeping is presented to reduce maneuver costs. By considering both the solar gravity and radiation pressure in a nominal LPO design, station-keeping simulations about fuel consumption for real LPOs around both collinear and triangular libration points are performed in a high-fidelity ephemeris model. Results show the effectivity of the modified strategy with total maneuver costs reduced by greater than 10% for maintaining triangular LPOs.

scholarly journals Periodic Attitudes of Libration Point Spacecrafts in the Earth-Moon System

2020 ◽  
Vol 2020 ◽  
pp. 1-10
Author(s):  
Qiwei Guo ◽  
Bo Xu ◽  
Hanlun Lei
Keyword(s):  
Body Problem ◽  
Libration Point ◽  
Space Mission ◽  
Attitude Motion ◽  
Three Body Problem ◽  
Moon System ◽  
Libration Point Orbits ◽  
The Earth ◽  
Rigid Spacecraft ◽  
Three Body

The attitude motion of a rigid spacecraft is studied in the Earth-Moon circular restricted three-body problem. Firstly, the equilibrium attitude and its stability as functions of the moments of inertia are discussed when the spacecraft is assumed at the libration points. Then, periodic attitudes of a spacecraft with mass distribution given in the stable regions are obtained. Regarding space mission applications, the Sun orientation is discussed, and the orbit-attitude resonances are constructed for spacecrafts working on the libration point orbits by means of a continuation procedure.

A Framework for Constructing Transfers Linking Periodic Libration Point Orbits in the Spatial Circular Restricted Three-Body Problem

2016 ◽  
Vol 26 (05) ◽  
pp. 1630013 ◽  
Author(s):  
Amanda F. Haapala ◽  
Kathleen C. Howell
Keyword(s):  
Body Problem ◽  
Libration Point ◽  
Mass Parameter ◽  
Solar Radiation Pressure ◽  
Restricted Three Body Problem ◽  
Three Body Problem ◽  
Libration Point Orbits ◽  
The Earth ◽  
Three Body ◽  
Fidelity Model

The Earth–Moon libration points are of interest for future missions and have been proposed for both storage of propellant and supplies for lunar missions and as locations to establish space-based facilities for human missions. Thus, further development of an available transport network in the vicinity of the Moon is valuable. In this investigation, a methodology to search for transfers between periodic lunar libration point orbits is developed, and a catalog of these transfers is established, assuming the dynamics associated with the Earth–Moon circular restricted three-body problem. Maneuver-free transfers, i.e. heteroclinic and homoclinic connections, are considered, as well as transfers that require relatively small levels of [Formula: see text]. Considering the evolution of Earth–Moon transfers as the mass parameter is reduced, a relationship emerges between the available transfers in the Earth–Moon system and maneuver-free transfers that exist within the Hill three-body problem. The correlation between transfers in these systems is examined and offers insight into the existence of solutions within the catalog. To demonstrate the persistence of the catalog transfers in a higher-fidelity model, several solutions are transitioned to a Sun–Earth–Moon ephemeris model with the inclusion of solar radiation pressure and lunar gravity harmonics. The defining characteristics are preserved in the high-fidelity model, validating both the techniques employed for this investigation and the solutions computed within the catalog.

scholarly journals GEOMETRY OF HOMOCLINIC CONNECTIONS IN A PLANAR CIRCULAR RESTRICTED THREE-BODY PROBLEM

2007 ◽  
Vol 17 (04) ◽  
pp. 1151-1169 ◽  
Author(s):  
MARIAN GIDEA ◽  
JOSEP J. MASDEMONT
Keyword(s):  
Symbolic Dynamics ◽  
Body Problem ◽  
Invariant Manifolds ◽  
Libration Point ◽  
Homoclinic Orbits ◽  
Restricted Three Body Problem ◽  
Three Body Problem ◽  
Lyapunov Orbits ◽  
Homoclinic Connections ◽  
Three Body

The stable and unstable invariant manifolds associated with Lyapunov orbits about the libration point L1between the primaries in the planar circular restricted three-body problem with equal masses are considered. The behavior of the intersections of these invariant manifolds for values of the energy between that of L1and the other collinear libration points L2, L3is studied using symbolic dynamics. Homoclinic orbits are classified according to the number of turns about the primaries.

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