NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Access to Mars from Earth-Moon Libration Point Orbits:This investigation is focused specifically on transfers from Earth-Moon L(sub 1)/L(sub 2) libration point orbits to Mars. Initially, the analysis is based in the circular restricted three-body problem to utilize the framework of the invariant manifolds. Various departure scenarios are compared, including arcs that leverage manifolds associated with the Sun-Earth L(sub 2) orbits as well as non-manifold trajectories. For the manifold options, ballistic transfers from Earth-Moon L(sub 2) libration point orbits to Sun-Earth L(sub 1)/L(sub 2) halo orbits are first computed. This autonomous procedure applies to both departure and arrival between the Earth-Moon and Sun-Earth systems. Departure times in the lunar cycle, amplitudes and types of libration point orbits, manifold selection, and the orientation/location of the surface of section all contribute to produce a variety of options. As the destination planet, the ephemeris position for Mars is employed throughout the analysis. The complete transfer is transitioned to the ephemeris model after the initial design phase. Results for multiple departure/arrival scenarios are compared.
Document ID
20150000152
Document Type
Preprint (Draft being sent to journal)
Authors
Kakoi, Masaki (Purdue Univ. West Lafayette, IN, United States)
Howell, Kathleen C. (Purdue Univ. West Lafayette, IN, United States)
Folta, David (NASA Goddard Space Flight Center Greenbelt, MD United States)
Date Acquired
January 5, 2015
Publication Date
April 21, 2014
Subject Category
Astrodynamics
Report/Patent Number
GSFC-E-DAA-TN15175
Funding Number(s)
CONTRACT_GRANT: NNX13AH02G
CONTRACT_GRANT: NNX13AE55G
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Dynamical Systems
Mars
Libration Point Orbit

Available Downloads

NameType 20150000152.pdf STI