Optimum rendezvous transfer between coplanar heliocentric elliptic orbits using solar sail

Details Optimum rendezvous transfer between coplanar heliocentric elliptic orbits using solar sail Optimum rendezvous transfer between coplanar heliocentric elliptic orbits using solar sail

Dec 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992jgcd...15.1507r&link_type=abstract

Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 15, no. 6, p. 1507-1509.

Physics

1

Elliptical Orbits, Rendezvous Trajectories, Solar Sails, Trajectory Optimization, Transfer Orbits, Algorithms, Interplanetary Flight, Mercury (Planet), Spacecraft Motion

Scientific paper

A convenient formulation is presented for determining the effect of terminal orbit eccentricities on the steering profile of a sail spacecraft for time-optimal rendezvous transfer between coplanar heliocentric orbits. The problem is reduced to that of solving a two-point boundary value problem for a system of seven ordinary differential equations. The system is solved using the controlled random search optimization technique.

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