Desiging trajectories in a planetmoon environment using the controlled Keplerian map
Journal of Guidance, Control, and Dynamics 32(2), 436443.
Piyush Grover and
Shane D. Ross
Engineering Science and Mechanics, Virginia Polytechnic Institute and State University
ABSTRACT
Designing fuel efficient trajectories which visit different moons of a planetary system is best handled by breaking up the problem into multiple threebody problems. This approach, called the patched threebody approach has received considerable attention in recent years, and has proved to lead to substantial fuel savings compared to the traditional patchedconic approach. We consider the problem of designing fuelefficient multimoon orbiter spacecraft trajectories in the JupiterEuropaGanymedespacecraft system with realistic transfer times. Fueloptimal (i.e., near zero fuel) trajectories without using any control are first determined but turn out to be infeasible due to very long transfer times involved. We then describe a methodology which exploits the underlying structure of the dynamics of the two threebody problems, i.e., JupiterEuropaSpaceraft and JupiterGanymedeSpacecraft, using the Hamiltonian structurepreserving Keplerian map approximations derived earlier and using small control inputs in the form of instantaneous DeltaVs to get trajectories with timesofflight on the order of months rather than several years. A typical trajectory constructed using the control algorithm can complete the mission in about 10% of the timeofflight of an uncontrolled trajectory.
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