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Multiobjective genetic optimization of Earth-Moon trajectories in the restricted four-body problem

Assadian, N ; Sharif University of Technology | 2010

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  1. Type of Document: Article
  2. DOI: 10.1016/j.asr.2009.10.023
  3. Publisher: 2010
  4. Abstract:
  5. In this paper, optimal trajectories of a spacecraft traveling from Earth to Moon using impulsive maneuvers (ΔV maneuvers) are investigated. The total flight time and the summation of impulsive maneuvers ΔV are the objective functions to be minimized. The main celestial bodies influencing the motion of the spacecraft in this journey are Sun, Earth and Moon. Therefore, a three-dimensional restricted four-body problem (R4BP) model is utilized to represent the motion of the spacecraft in the gravitational field of these celestial bodies. The total ΔV of the maneuvers is minimized by eliminating the ΔV required for capturing the spacecraft by Moon. In this regard, only a mid-course impulsive maneuver is utilized for Moon ballistic capture. To achieve such trajectories, the optimization problem is parameterized with respect to the orbital elements of the ballistic capture orbits around Moon, the arrival date and a mid-course maneuver time. The equations of motion are solved backward in time with three impulsive maneuvers up to a specified low Earth parking orbit. The results show high potential and capability of this type of parameterization in finding several Pareto-optimal trajectories. Using the non-dominated sorting genetic algorithm with crowding distance sorting (NSGA-II) for the resulting multiobjective optimization problem, several trajectories are discovered. The resulting trajectories of the presented scheme permit alternative trade-off studies by designers incorporating higher level information and mission priorities
  6. Keywords:
  7. Ballistic capture ; Earth to Moon transfer ; Celestial bodies ; Crowding distance ; Earth parking orbits ; Flight time ; Four-body problem ; Genetic optimization ; Gravitational fields ; High potential ; Higher-level information ; Multi objective ; Multi-objective optimization problem ; Multi-objective trajectory optimization ; Non-dominated sorting genetic algorithms ; NSGA-II ; Objective functions ; Optimal trajectories ; Optimization problems ; Orbital element ; Parameterized ; Pareto-optimal ; Restricted four-body problem (R4BP) ; Trade-off study ; Aerodynamics ; Ballistics ; Equations of motion ; Force measurement ; Gravitation ; Multiobjective optimization ; Pareto principle ; Spacecraft ; Three dimensional ; Time varying systems ; Trajectories ; Moon
  8. Source: Advances in Space Research ; Volume 45, Issue 3 , February , 2010 , Pages 398-409 ; 02731177 (ISSN)
  9. URL: http://www.sciencedirect.com/science/article/pii/S0273117709006863