Spacecraft trajectory design utilizing resonance orbits in a hybrid optimal control framework

Optimal trajectories;Resonance orbits;Hybrid optimal control

Bunce, Devin T ; Ghosh ; Alexander R. M.

关键词: Optimal trajectories;    Resonance orbits;    Hybrid optimal control;   

Others  :  https://www.ideals.illinois.edu/bitstream/handle/2142/99268/BUNCE-THESIS-2017.pdf?sequence=1&isAllowed=y

美国|英语

来源: The Illinois Digital Environment for Access to Learning and Scholarship

【 摘 要 】

Low-energy trajectories are a growing subset of trajectory design, particularly in the three-body space. These trajectories use the inherent stability and instability of certain orbits as a means of fuel efficient transfers. Traditionally, work on these types of trajectories has taken a very “hands on” approach from the astrodynamicist, i.e. requiring intuition and fine tweaking of parameters. This work details preliminary efforts to incorporate resonance orbits, their invariant manifolds, and associated families into an automated global optimization tool in order to create solutions of optimal impulsive spacecraft trajectories in multi-body environments. Previous work using this tool has shown the ability to use other key dynamical structures of the circular restricted three-body problem (e.g. Euler-Lagrange point orbits and their invariant manifolds) within the same automated global optimization framework to produce low-energy trajectory solutions. This work outlines necessary dynamical systems theory. Described next is how to generate resonance orbits of the first species by providing examples of the Earth-Moon and Jupiter-Europa systems. Finally shown is how these structures are used within the optimization framework. Several non-trivial impulsive trajectory problems from low-Earth to resonance orbits, resonance to resonance transfers, and resonance to Euler-Lagrange point orbit transfers are shown with Pareto front solutions.