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

Arab Kermani, Mojtaba | 2014

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 45954 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Nobahari, Hadi
  7. Abstract:
  8. In this work, inertial guidance and control of an axisymmetric flying vehicle with a spinning part is performed based on dynamic modeling and seven degree of freedom simulation. Flying vehicle is composed of front and aft bodies and these bodies are connected to each other via a hydrodynamic bearing. Front body is roll isolated from the aft body and includes all necessary guidance and control equipments such as sensors, canard set and so on. The control fins, located on the nose, is used to control the roll angle of the nose and to execute the lateral acceleration commands. Also, the aft body is freely rolling and includes the stabilizing fins. In this project, the translational and rotational equations of motion are developed using Newton’s second law and Euler law. After modeling the aerodynamic and propulsion disciplines, the transfer functions, required to design of the control loops, are obtained. Then, using the linear control theory, roll, pitch and yaw controllers are designed. Also, guidance algorithms are constructed using pure proportional navigation law. The performance of the different parts such as guidance and control system is evaluated using a nonlinear seven degree of freedom simulation. Finally, in other to minimize miss distance and control effort, integrated optimization of the guidance and control parameters is performed using TCACS algorithm
  9. Keywords:
  10. Inertial Navigation System ; Dual Spin Flying Vehicle ; Axisymmetric Flying Vehicle ; proportional Guidance ; Integrated Optimization ; Tabu Search Algorithm ; Continuous Ant Colony System

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