Neural extended kalman filter based angle-only target tracking for cruise missiles

Download

index.pdf

Date

2016

Author

Eşsiz, Görkem

Metadata

Show full item record

Item Usage Stats

356
views

159
downloads

This thesis presents an adaptive roll control scheme for guided munitions. Guided munitions are air-to-air or air-to-surface weapons which have enhanced target hit capabilities with laser seekers or similar guidance utilities. The dynamic interferences in nonlinear regions of the flight envelope, leads the studies on control of guided munitions to search for adaptive solutions. The missile used in this study has no propulsive forces and do the adequate maneuvers commanded by the guidance algorithm with its initial kinetic and potential energy. In this study first, the baseline roll autopilot is developed which is in cascaded two loop architecture augmented with a feedforward controller and a model reference controller structure. Since the coupling effects could not be eliminated with the baseline architecture, the control algorithm is improved with a model reference adaptive controller with Chebyshev polynomials based uncertainty parameterization. Then the study is extended by utilizing concurrent learning algorithm as the adaptation law to learn and reveal the unknown pitch-roll couplings.

Subject Keywords

Cruise missiles., Guided missiles., Kalman filtering., Projectiles, Aerial., Tracking (Engineering)., Guided missiles

URI

http://etd.lib.metu.edu.tr/upload/12619792/index.pdf
https://hdl.handle.net/11511/25466

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Adaptive roll control of guided munitions Öveç, Naz Tuğçe; Kutay, Ali Türker; Department of Aerospace Engineering (2016) This thesis presents an adaptive roll control scheme for guided munitions. Guided munitions are air-to-air or air-to-surface weapons which have enhanced target hit capabilities with laser seekers or similar guidance utilities. The dynamic interferences in nonlinear regions of the flight envelope, leads the studies on control of guided munitions to search for adaptive solutions. The missile used in this study has no propulsive forces and do the adequate maneuvers commanded by the guidance algorithm with its ...
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...
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 ...
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 ...
Response surface based performance analysis of an air-defense missile system Günaydın, Kerem; Tekinalp, Ozan; Department of Aerospace Engineering (2014) In this thesis, response surface based performance analysis of an air defense missile system was performed. System performance defined as the probability of hit is determined using a conventional grid analysis in order to set up a control group. Then, some experiments were designed to construct response surfaces (RSM). Simulation model was run for these experiment points. Response surfaces for the whole operational area of an air defense missile system is developed using these experiments, so as to be able ...

Citation Formats

G. Eşsiz, “Neural extended kalman filter based angle-only target tracking for cruise missiles,” M.S. - Master of Science, Middle East Technical University, 2016.