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    • Keywords


      Low thrust; trajectory optimization; differential evolution

    • Abstract


      Transfers from geosynchronous transfer orbits (GTO) to geosynchronous orbits (GSO) using electric propulsion have been optimized in the current study. Both time-optimal and fuel-optimal trajectories are generated. Three-dimensional equations of motion are considered for the system dynamics. The indirect approach based on optimal control theory is followed and the resulting two-point boundary value problem is solved using differential evolution, a search-based global optimization technique. Optimal trajectories for various mission scenarios are obtained using differential evolution and compared to transfers presented in literature.

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    • Author Affiliations



      1. Vikram Sarabhai Space Centre, Thiruvananthapuram, India
      2. Indian Institute of Space Science and Technology, Thiruvananthapuram, India
    • Dates

  • Sadhana | News

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