Future space missions will depend more on low-thrust propulsion (such as ion engines) thanks to its high specific impulse. Yet, the design of low-thrust trajectories is complex and challenging. Third-body perturbations often dominate the thrust, and a significant change to the orbit requires a long duration of thrust. In order to guide the early design phases, we have developed an efficient and efficacious method to obtain approximate propellant and flight-time requirements (i.e., the Pareto front) for orbit transfers. A search for the Pareto-optimal trajectories is done in two levels: optimal thrust angles and locations are determined by Q-law, while the Q-law is optimized with two evolutionary algorithms: a genetic algorithm and a simulated-annealing-related algorithm. The examples considered are several types of orbit transfers around the Earth and the asteroid Vesta.


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    Titel :

    Design and Optimization of Low-thrust Orbit Transfers Using Q-law and Evolutionary Algorithms


    Beteiligte:

    Kongress:

    IEEE Aerospace Conference ; 2005 ; Big Sky, MT, United States


    Erscheinungsdatum :

    2005-03-05


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch




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