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Integrated Impulsive Maneuver and Propulsion System Design for Upper Stages Guidance of Spacecrafts

Zarezade, Ali | 2009

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 39945 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Pourtakdoust, Hossain
  7. Abstract:
  8. This work is an attempt toward an integrated preliminary design of solid rocket (SR) propulsion system for impulsive orbital maneuvers. In this regard a comparative study is initially performed classifying current space propulsion systems and along the goals of this thesis, solid rocket system was selected for our integrated approach. Subsequently, two integration schemes were studied that differed in the primacy of the two design tasks. This study directed our focus to initially size and design an ideal rocket engine and refine it through integration with the maneuver design. Utilizing the ideal rocket concept and its governing equations, a SR was designed to provide the required total impulse of the maneuver as well as the other design criteria. The engine was next simulated to determine its thrust profile and other related performance parameters using an internal ballistics simulation code. The engine characteristics together with the nonlinear modified Kepler equations allowed us to formulate the problem for the determination of guidance strategy. This last task was performed using variational approach as well as Genetic algorithm. Results of the two methods in terms of the required guidance angle were in complete agreement and the transfer maneuver to target orbit occurred within a predefined error.

  9. Keywords:
  10. Optimal Control ; Genetic Algorithm ; Steepest Descent Method ; Solid Propellant Rocket ; impulsive Maneuver

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