Designing an Optimal Control LQT for Controlling and Guidance of Missile
DOI:
https://doi.org/10.12962/j25796216.v2.i1.36Abstract
Missile has to be controlled and follow the commanded guidance in order to make its flight hit the target. Since missile has a nonlinear characteristic and coupled dynamic equation, controlling a missile has become more complex. Linear Quadratic Tracking (LQT) is one of optimal control theory where its objective is to make the output of a system tracks its reference as close as possible while minimize or maximize a desired performance index. In this paper, an autopilot for missile is designed which consists nonlinear state feedback decoupler and LQT controller. Pursuit Guidance is used for the guidance law. A missile-target engagement simulation is created using 2 kinds of target; static target and dynamic target. By using static target, the mean of the closest distance between missile and the target is 0.45 meters and by using dynamic target the mean of the closest distance between missile and the target is 2.562 meters. Keywords: guided missile, Linear Quadratic Tracking, Nonlinear State Feedback Decoupler, Pursuit GuidanceReferences
B. Özkan, “Dynamic Modeling, Guidance, and Control of Homing Missiles,†Dec. 2017.
G. M. Siouris, Missile Guidance and Control Systems. Springer New York, 2010.
G. M. Siouris, Aerospace Avionics Systems: A Modern Synthesis. Academic Press, 1993.
P. H. Zipfel, Modeling and Simulation of Aerospace Vehicle Dynamics. American Institute of Aeronautics and Astronautics, 2007.
A. K. R. Effendi, M. Rameli, E. Iskandar, and M. Baihaqi, “Linearization and decoupling controller for quadruple tank,†in 2017 International Seminar on Intelligent Technology and Its Applications (ISITIA), 2017, pp. 233–237.
F. L. Lewis, D. Vrabie, and V. L. Syrmos, Optimal Control, Third. New Jersey: John Wiley & Sons, 2012.
W. Bużantowicz, “Matlab Script for 3D Visualization of Missile and Air Target Trajectories,†vol. 5, pp. 419–422, Sep. 2016.
