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Optimal Online Guidance Algorithm of the Flexible Launch Vehicle under the Occurrence of Random Failure in the Propulsion System in Order to Inject the Satellite into the Orbit

Khalvandi, Ali | 2024

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 57684 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Fathi, Mohsen
  7. Abstract:
  8. The purpose of this thesis is to provide an optimal and online flexible launch vehicle guidance algorithm and method under the occurrence of a random failure in the propulsion system in order to inject the satellite in the nominal orbit/the closest orbit to the nominal orbit. In addition, by recognizing the effects caused by the fault in the propulsion system on the flight dynamics of the launch vehicle, appropriate guidance decisions are applied in analyzes and calculations, and the flexible launch vehicle, according to the amount of error and the time of occurrence of the error and the amount of time left to reach the rated orbit, reaches the nominal orbit or the closest orbit to the nominal orbit under the optimal online guidance command. Therefore, several examples of optimal and online guidance methods are compared and the best example is selected and applied. When a fault occurs in the propulsion system, the amount of difference between the orbital elements compared to the nominal orbit should be minimized and the control effort to reach the destination orbit should be optimal. Due to the fact that in the event of a propulsion system error, it is necessary to design a fast online trajectory and the faster this trajectory is designed at the moment of failure, the better its efficiency, fast trajectory design using the Gaussian pseudo-spectral method will be used
  9. Keywords:
  10. Flexible Launch Vehicle ; Optimal Trajectory ; Thrust Loss ; Satellite Injection ; Online Guidance ; Random Failure

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