Two new switching surface design techniques for nonlinear systems with their applications to missile control

Download
1999
Salamcı, Metin Uymaz

Suggestions

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...
A novel flight control algorithm for multicopters
Tekinalp, Ozan (null; 2016-09-29)
A new nonlinear control algorithm is proposed for multi-copter type vertical takeoff vehicles. The algorithm uses linear controllers for the position control in the outer loop. The inner loop attitude control is carried out using quaternion representation. The necessary thrust vector requirements of the position control are converted to inner loop as attitude control commands. The inner loop uses a Lyapunov function based attitude controller utilizing the to-go quaternion calculated from thrust vector comma...
Linear Analysis of Zero-Lift Pitching Moment Coefficient and Gravity Effects on Missile Autopilots
Ovec, Naz T.; Erer, Koray S.; Kutay, Ali Türker (2015-03-14)
The most of the studies on disturbance rejection are covered with robust control methods, where this paper suggests a narrowed but a more simplified linear model based technique to assess the robustness of the controllers. In this paper presented, the problems originated from the disturbances are aimed to be obtained as far in advance as possible. The method used in this work reduces the iterative fine tuning time course between the non-linear simulation and the linear model; hence it enhances the authority...
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 ...
Faux Riccati equation techniques for feedback control of nonlinear and time-varying systems
Prach, Anna; Tekinalp, Ozan; Bernstein, Dennis; Department of Aerospace Engineering (2015)
Rapid development of nonlinear control theory for application to challenging and complex problems is motivated by the fast technological development and demand for highly accurate control systems. In infinite-horizon nonlinear optimal control the essential difficulty is that no efficient analytical or numerical algorithm is available to derive exact expressions for optimal controls. This work concerns the numerical investigation of faux Riccati equation methods for control of nonlinear and linear time-varyi...
Citation Formats
M. U. Salamcı, “Two new switching surface design techniques for nonlinear systems with their applications to missile control,” Ph.D. - Doctoral Program, Middle East Technical University, 1999.