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Optimal Transfer Trajectory Design to Halo Orbits Using Homotopy Approach

Heydari, Ghasem | 2019

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 51598 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Pourtakdoust, Hossein; Kiani, Maryam
  7. Abstract:
  8. Optimal Maneuvering to lessen the required fuel or to speed up the mission operation time is a significant part of various space missions. Optimal performance of a spacecraft reduces the mission cost, increases the mission life time and subsequently provides more chances for space exploration. In this sense, optimal maneuvering has always been at the center of attention and abundant works have been assigned to this importance. This research is also devoted to optimal trajectory design to transfer from low Earth orbits to the halo orbits. Specific characteristics of the halo orbits including periodicity, geometry, and particular position around the collinear liberation points of the restricted three-body problem have made them attractive to place telescopes like James Webb to ease and broaden space observations. It is obvious that mathematical tools of optimization could affect the optimal solution of a problem. Homotopy approach is an effective strategy to achieve the solution of a difficult problem through deformation of a simple problem. Considering complex dynamics of the halo orbits plus troubles of fuel minimization problem, a continuation homotopy method is adopted in this thesis to achieve the optimal solution via transformation of a minimum energy problem. It is proven that the homotopy approach is an efficient method to handle complex optimization problems like the present optimal trajectory design to transfer from LEO to halo orbits around L2 point of the Earth-moon system
  9. Keywords:
  10. Optimal Mission Design ; Transfer Trajectory Design ; Transfer Into Halo Orbit ; Homotopy Theory ; Halo Orbits ; Optimal Control

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