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Fin Failure Tolerant Control of Agile Supersonic Flight Vehicle

Ashrafifar, Asghar | 2020

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  1. Type of Document: Ph.D. Dissertation
  2. Language: Farsi
  3. Document No: 52903 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Fathi Jegarkandi, Mohsen
  7. Abstract:
  8. To make it easier to transition and increase the number of missiles on the launcher, many missiles consider the fins are designed to be foldable. Also, these types of fins can be opened during the flight and therefore reduce the drag force in the initial phase of the flight. One of the disadvantages of this type of design is that the fins may not open during the flight. Moreover, locking the actuator, breaking or destroying some part or all of the control surface of supersonic aircraft due to high speed and temperature and loss of thermal insulation is very probable. This thesis considers the locking, not opening, or even breaking the control surfaces, as well as the destruction of some part of them. Absence of a fin, either by not opening it or by breaking it, will cause asymmetries and changes in the dynamic equations of the device due to changes in the aerodynamic model of the device. Also, when a fin is locked or damaged, the remaining three fins must be accountable to produce the required control moments. The purpose of this thesis is to detect the failure and design a tolerant control against the mentioned failures. To this purpose, an equivalent aerodynamic model is proposed to express the dynamics of the vehicle and the health of each fin is monitored by the value of a parameter, which is estimated using an adaptive robust filter. Then, using the separation theory, the dynamic system is divided into the fast and slow subsystems and the control signal is designed for the failure dynamics using backstepping theory. Moreover, the control allocation over the condition of the fins will change to produce the desired control moment. Besides, the fin failure in the integrated guidance and control problem is also investigated in this thesis. To design a fin failure tolerant controller in this case, a combined backstepping and sliding mode control scheme is exploited
  9. Keywords:
  10. Nonlinear Control ; Nonlinear Filters ; Integrated Guidance and Control (IGC) ; Aerodynamic Estimation ; Fin Failure Tolerant Control ; Missile Fin Failure

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