Three-stage approach to optimal low-thrust earth-moon trajectories

Details Three-stage approach to optimal low-thrust earth-moon trajectories Three-stage approach to optimal low-thrust earth-moon trajectories

Nov 1994

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994jgcd...17.1275p&link_type=abstract

Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 17, no. 6, p. 1275-1282

Computer Science

3

Earth-Moon Trajectories, Low Thrust Propulsion, Orbital Mechanics, Three Body Problem, Trajectory Optimization, Transfer Orbits, Boundary Conditions, Circular Orbits, Low Earth Orbits, Lunar Orbits, Parking Orbits

Scientific paper

Minimum-fuel, planar trajectories from a circular low earth parking orbit to circular low lunar parking orbit with a fixed thrust-coast-thrust engine sequence are computed for a low-thrust spacecraft. The problem is studied in the context of the classical restricted three-body problem: (1) to obtain several optimal continuous-thrust earth-escape and moon trajectories; (2) to compute a suboptimal, all-coasting, translunar trajectory between boundary conditions provided by the first subproblem; and (3) the competence trajectory is solved using a 'hybrid' direct/indirect method. Numerical results are presented for the optimal earth-moon trajectories.

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