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Robust Control of Reentry Vehicle Based on Nonlinear Dynamic Inversion Method

Saeedi Hamzeh Khanloo, Hossein | 2019

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 52427 (02)
  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 design a controller for a reentry spacecraft to despite the uncertainty in the initial conditions and the aerodynamic characteristics as well as the presence of atmospheric turbulence and the presence of noise in the system. Reentry vehicle that studying in this project is Apollo, a capsule without wings, with a low lift to drag ratio. Earth is modeled as elliptical and Earth's rotation is also considered. The Guidance system produces the bank angle command, and the reentry vehicle must follow the commands with the help of the controller. The controller is designed based on the nonlinear dynamic inversion method. Dynamic and kinematic equations of rotational motion are individually reversed and two control loops are created. Because the nonlinear dynamic inversion method is sensitive to some modeling uncertainties, we use sliding mode control to compensate errors of this linearization theory. In other words, in order to compensate the errors that affect the function of the system, the sliding mode control is added to the control structure. At the end, system performance is evaluated despite uncertainties in initial conditions, aerodynamic coefficients, moments of inertia and mass.Also system performance is evaluated when there is atmospheric disturbances and noise in the system
  9. Keywords:
  10. Reentry to Atmosphere ; Nonlinear Dynamic Inversion Control ; Sliding Mode Control ; Apollo Guiding ; Uncertainty ; Apollo Control

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