The effect of parking orbit constraints on the optimization of ballistic planetary trajectories

Details The effect of parking orbit constraints on the optimization of ballistic planetary trajectories The effect of parking orbit constraints on the optimization of ballistic planetary trajectories

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984adans..54...85s&link_type=abstract

IN: Astrodynamics 1983; Proceedings of the Conference, Lake Placid, NY, August 22-25, 1983. Part 1 (A84-30526 13-13). San Diego,

Computer Science

Performance

Ballistic Trajectories, Parking Orbits, Space Missions, Spacecraft Trajectories, Trajectory Optimization, Asteroid Missions, Constraints, Launch Vehicles, Mission Planning, Performance Prediction

Scientific paper

The optimization of ballistic planetary trajectories is developed which includes constraints on departure parking orbit inclination and node. This problem is formulated to result in a minimum total Delta V where the entire constrained injection Delta V is included in the optimization. An additional Delta V is also defined to allow for possible optimization of parking orbit inclination when the launch vehicle orbit capability varies as a function of parking orbit inclination. The optimization problem is formulated using primer vector theory to derive partial derivatives of total Delta V with respect to possible free parameters. Minimization of total Delta V is accomplished using a quasi-Newton gradient search routine. The analysis is applied to an Eros rendezvous mission whose transfer trajectories are characterized by high values of launch asymptote declination during particular launch opportunities. Comparisons in performance are made between trajectories where parking orbit constraints are included in the optimization and trajectories where the constraints are not included.

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