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Integrated Terminal Guidance and Control of an Axisymmetric Flying Vehicle with a Spinning Part

Karimi, Samine | 2016

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 48374 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Nobahari, Hadi; Fathi, Mohsen
  7. Abstract:
  8. In this research, a Ground-to-Ground axisymmetric flying vehicle is studied. In this flying vehicle the warhead is replaced by a nose having simple and cheap guidance and control. Commonly such systems include axial rotation to increase stability, which results in the malfunction of the added seekers. In this research, to overcome this problem, the rotation of the vehicle’s forward part is controlled by fuzzy control method, from the beginning of the fly. In addition, a strapdown seeker, which has high accuracy and low cost is used. This provides the system with employing Integrated Guidance and Control (IGC). The IGC, used in this research is based on fuzzy logic, which directly determines the deflection values of the control surfaces. The guidance and control of the pitch and yaw channels, which is activated in the terminal phase decreases the error angle between line of sight and the body x-axis gradually. Moreover, a 7DOF simulation model is used for designing the guidance and control algorithms. In order to achieve maximum accuracy and proper deflection angles, an optimization algorithm optimizes the effective parameters of guidance and control. Finally an error analysis is included. The results show that by using a simple and cheap IGC for a dual spin flying vehicle with specific dynamics, in the terminal phase, small miss distance and high performance are obtained. Furthermore, in the aforementioned system using a seeker of strapdown kind is for the first time
  9. Keywords:
  10. Integrated Guidance and Control (IGC) ; Fuzzy Logic ; Dual Spin Flying Vehicle ; Integrated Guidance and Control (IGC) ; Optimum Scheme

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