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Integrated Robust Guidance and Control of VTVL Reusable Launch Vehicle at Terminal Phase Using Sliding Mode Control

Asadi Azghan, Babak | 2021

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 53875 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Fathi Jegarkandi, Mohsen
  7. Abstract:
  8. In this article, guidance and control of reusable launch vehicle at terminal phase has been studied. The goal of this article is increasing the accuracy and safety of the guidance and control system of the launch vehicle in order to successfully land on ground surface. Integrated guidance and control, being a novel method in guidance and control, is used to guide the launch vehicle in the re-entry phase and landing phase on ground surface. The returning object studied is a Falcon 9 rocket for which we find the 6 DOF model. The landing method of this vehicle is vertical. Implementing an integrated guidance and control system is a novel approach in this area. The controller used in this article is based on sliding-mode. This controller has an acceptable performance against the uncertainties and indefinite values of the system parameters. GPOPS software is used to create the initial flight path of the launch vehicle. This software calculates the optimal landing path with respect to dynamic constraints, control constraints and a cost function. Genetic algorithm is used to find the constant parameters for guidance and control. Results show that integrated guidance and control needs less bulk standard deviation than common guidance and control due to simultaneous solving of guidance and control equations. This causes the defined constraints not to surpass the acceptable values anywhere in the path
  9. Keywords:
  10. Integrated Guidance and Control (IGC) ; Launch Vehicle ; Genetic Algorithm ; Sliding Mode Controller ; Reusable Launch Vehicle ; GPOPS Software

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