TY - GEN

T1 - Optimal low-thrust/invariant manifold Earth Moon transfer trajectories

AU - Martin, Christopher S.

AU - Conway, Bruce A

PY - 2010

Y1 - 2010

N2 - Minimum-time and hence minimum-fuel trajectories are found for a spacecraft using continuous low-thrust propulsion to leave geosynchronous transfer orbit and enter a low-lunar orbit, transiting via the stable and unstable manifolds of a periodic orbit about the interior Earth-Moon Lagrange point. The optimizer chooses the thrust pointing angle time history, the points of arrival/departure from the stable and unstable manifold respectively and the size of the halo orbits, in order to minimize the powered flight time. The arrival position and velocity matching conditions are obtained from a parameterization of the orbit using cubic splines since no analytic description of the manifolds exist.

AB - Minimum-time and hence minimum-fuel trajectories are found for a spacecraft using continuous low-thrust propulsion to leave geosynchronous transfer orbit and enter a low-lunar orbit, transiting via the stable and unstable manifolds of a periodic orbit about the interior Earth-Moon Lagrange point. The optimizer chooses the thrust pointing angle time history, the points of arrival/departure from the stable and unstable manifold respectively and the size of the halo orbits, in order to minimize the powered flight time. The arrival position and velocity matching conditions are obtained from a parameterization of the orbit using cubic splines since no analytic description of the manifolds exist.

UR - http://www.scopus.com/inward/record.url?scp=80053392804&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=80053392804&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:80053392804

SN - 9780877035602

T3 - Advances in the Astronautical Sciences

SP - 89

EP - 106

BT - Spaceflight Mechanics 2010 - Advances in the Astronautical Sciences

T2 - AAS/AIAA Space Flight Mechanics Meeting

Y2 - 14 February 2010 through 17 February 2010

ER -