Design of an Intelligent Aerodynamic Control System for Spinning Flight Vehicles

Please enable javascript in your browser.

Mohammadkarimi, Hamed | 2009

695 Viewed

Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 39893 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Nobahari, Hadi
Abstract:
Spinning vehicles are a large category of aerospace vehicles including shoulder launched missiles, intelligent anti-armor projectiles, guided rockets and some of re-entry vehicles, anti tank missiles and satellites. This thesis presents the problems of guidance and control in a spinning vehicle with a single plane of On-Off control surface. The missile uses this single surface to control both yaw and pitch channels. The actuator used in this missile is a discrete On-Off type which makes the missile behavior nonlinear. Using describing function technique, a linear model of the spinning missile dynamics in the presence of an On-Off actuator is derived and a classic controller is designed according to it. Guidance law in spinning missiles is studied and implementation problems are discussed. The obtained results are verified with a 4DOF simulation program. Since the plant is nonlinear, using nonlinear theories of control, can improve the system behavior. Thus, a fuzzy controller is designed and it was shown that the fuzzy controller improves the missile response in comparison with the classic controller
Keywords:
Guidance ; Fuzzy Control ; Describing Functions ; Spinning Flight Vehicle ; Single Channel Controller

No TOC