A procedure has been developed which minimizes total delta-V (instantaneous velocity change) for a multiple flyby trajectory with constraints on flyby altitude and orientation. The solution is found by varying the locations of maneuver points between each flyby to minimize the delta-Vs at the maneuver points. Each trajectory segment connecting consecutive maneuver points is found by solving an N-body analog to Lambert's problem. Multiconic techniques are used for trajectory propagation and for computation of the state transition matrix. The constrained parameter optimization problem is converted to an unconstrained problem by means of penalty functions and then solved with a quasi-Newton algorithm utilizing analytic first derivatives. This procedure has been successfully applied to Galileo satellite tour trajectories.
Optimization of multiple flyby trajectories
American Astronautical Society and American Institute of Aeronautics and Astronautics, Astrodynamics Specialist Conference ; 1979 ; Provincetown, MA
1979-06-01
Conference paper
No indication
English
Design of High-Accuracy Multiple Flyby Trajectories Using Constrained Optimization
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