Intelligent tracking and guidance system for swift target manoeuvres under nonparametric uncertainty

Adaptive control of guided missiles Tiryaki Kutluay, Kadriye; Yavrucuk, İlkay; Department of Aerospace Engineering (2011) This thesis presents applications and an analysis of various adaptive control augmentation schemes to various baseline flight control systems of an air to ground guided missile. The missile model used in this research has aerodynamic control surfaces on its tail section. The missile is desired to make skid to turn maneuvers by following acceleration commands in the pitch and yaw axis, and by keeping zero roll attitude. First, a linear quadratic regulator baseline autopilot is designed for the control of the...
Dynamic modeling and control of a hybrid fin actuation system for an air-to-air missile Çelik, Tayfun; Ciğeroğlu, Ender; Yazıcıoğlu, Yiğit; Department of Mechanical Engineering (2014) Air-to-air missiles require high maneuverability. In order to obtain high maneuverability, hybrid fin actuation systems are used. In this study, a hybrid fin actuation system which is composed of aerodynamic control surfaces and thrust vector control is designed. Both aerodynamic and thrust vector control types are explained and the most suitable pair is determined for air-to-air missile. Then, the designed system is physically constructed and system identification procedure is performed. After that three d...
Fuzzy logic guidance system design for guided missiles Vural, A. Özgür; Özgören, Mustafa Kemal; Merttopçuoğlu, Osman; Department of Mechanical Engineering (2003) This thesis involves modeling, guidance, control, and flight simulations of a canard controlled guided missile. The autopilot is designed by a pole placement technique. Designed autopilot is used with the guidance systems considered in the thesis. Five different guidance methods are applied in the thesis, one of which is the famous proportional navigation guidance. The other four guidance methods are different fuzzy logic guidance systems designed considering different types of guidance inputs. Simulations ...
Active vibration control of complex structures in modal space Mersin, Kemal; Yazıcıoğlu, Yiğit; Şahin, Melin; Department of Mechanical Engineering (2014) Aerospace structures are designed to be light-weight to obtain high performance. Reduction in weight makes the structure flexible and lower frequency modes can be easily excited. Moreover those modes have low damping and vibrations do not attenuate immediately. Passive systems are effective to control the vibrations but they can be heavy and most of the time they do not respond to changing environment conditions. An active system is necessary for low-weight adaptive vibration reduction system. Modal Space C...
Missile autopilot design by projective control theory Doruk, Reşat Özgür; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2003) In this thesis, autopilots are developed for missiles with moderate dynamics and stationary targets. The aim is to use the designs in real applications. Since the real missile model is nonlinear, a linearization process is required to get use of systematic linear controller design techniques. In the scope of this thesis, the linear quadratic full state feedback approach is applied for developing missile autopilots. However, the limitations of measurement systems on the missiles restrict the availability of ...

Citation Formats

L. Gökkuş, “Intelligent tracking and guidance system for swift target manoeuvres under nonparametric uncertainty,” Ph.D. - Doctoral Program, Middle East Technical University, 1999.