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Near-optimal Trajectories for Microgravity Atmospheric Flights

Moradi, Sina | 2018

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 50664 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Malaek, Mohammad Bagher
  7. Abstract:
  8. In this Thesis, the necessary steps to implement near-optimal atmospheric flights in order to create micro and partial gravity condition has specified. This documentary has been prepared in a comprehensive way. The goal of this project is to reach the optimal throttle and elevator inputs and consequently optimal paths to perform the maneuver with maximum time. The basis of my work is to integrate two methods of tabu search and continuous ant colony system in order to find the best match for inputs. As a result, the aircraft’s proper inputs as a function of time can be accommodated. The constraints here refers to the safety of the flight, which are maximum operating speed, stall angle of attack, allowable load factor, etc.In this research, a complete maneuver cycle is divided into different segments that are cruise flight, pullup, transition, microgravity and safe exit. These flight phases are analyzed separately but they are finally integrated to ensure the continuity of the subject. However, there are other ways to control the load factor and perform the maneuver. A masterly use of cost functions can help us achieve an integrated trajectory. The result of this research in addition to achieve a microgravity environment for training crew of space missions along with testing equipment, is to investigate the potential of making new materials and compounds in orbital flights that have an impressive impact in various fields of study such as materials, combustion, fluid mechanics, medicine production, medical science, etc
  9. Keywords:
  10. Microgravity ; Heuristic Algorithm ; Trajectory Optimization ; Heuristic Algorithm ; Time Management ; Parabolic Flights ; Hybrid Heuristic Algorithm ; Flight Director

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