ARTICLE
A sliding mode controller design for a missile autopilot system
 
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Military University of Technology, Faculty of Mechatronics and Aerospace, Warsaw, Poland
Online publication date: 2020-01-15
Publication date: 2020-01-15
Submission date: 2018-06-25
Acceptance date: 2019-08-26
 
Journal of Theoretical and Applied Mechanics 2020;58(1):169–182
KEYWORDS
ABSTRACT
A description is given of an application of the sliding mode control (SMC) for stabilizing the static and dynamic characteristics of an anti-aircraft missile. The solution provides effective separation of the control process from the dynamics of the missile airframe. In the equivalent part of the stabilization system, a linear-quadratic regulator (LQR) is considered, and an analytical method of selecting the weighting elements of the gain matrix is proposed. This eliminates the need for an iterative solution of the Riccati equation. A nonlinear switching component is introduced into the control signal to provide smoothness of the system response. In simulation tests, the proposed solution was evaluated against selected quantity indices. The paper ends with observations and conclusions.
 
REFERENCES (14)
1.
Bużantowicz W., Pietrasieński J., 2018, Dual-control missile guidance: a simulation study, Journal of Theoretical and Applied Mechanics, 56, 3, 727-739.
 
2.
Çimen T., 2008, State-dependent Riccati equation (SDRE) control: a survey, Proceedings of the 17th IFAC World Congress, 41, 2, 3761-3775.
 
3.
Erdem E.B., Alleyne A.G., 2004, Design of a class of nonlinear controllers via state dependent Riccati equations, IEEE Transactions on Control Systems Technology, 12, 1, 133-137.
 
4.
Grycewicz H., Mosiewicz R., Pietrasieński J., 1984, Radio Control Systems (in Polish), Military University of Technology, Warsaw.
 
5.
Gu W., Zhao H., Pan C., 2005, Sliding mode control for an aerodynamic missile based on backstepping design, Journal of Control Theory and Applications, 3, 1, 71-75.
 
6.
Idan M., Shima T., Golan O.M., 2007, Integrated sliding mode autopilot-guidance for dual control missiles, Journal of Guidance, Control, and Dynamics, 30, 4, 1081-1089.
 
7.
Kurow V.D., Dołżanski J.M., 1964, Principles behind the Solid-Propellant Rocket Design (in Polish), Publishing House of Ministry of National Defense, Warsaw.
 
8.
Shima T., Idan M., Golan O.M., 2006, Sliding-mode control for integrated missile autopilot guidance, Journal of Guidance, Control, and Dynamics, 29, 2, 250-260.
 
9.
Shtessel Y.B., Tournes C.H., 2009, Integrated higher-order sliding mode guidance and autopilot for dual-control missiles, Journal of Guidance, Control, and Dynamics, 32, 1, 79-94.
 
10.
Siddiq M.K., Cheng F.J., Bo Y.W., 2013, SDRE based integrated roll, yaw and pitch controller design for 122 mm artillery rocket, Applied Mechanics and Materials, 415, 200-208.
 
11.
Siouris G.M., 2004, Missile Guidance and Control Systems, Springer, New York.
 
12.
Zhou D., Mu Ch., Xu W., 1999, Adaptive sliding-mode guidance of a homing missile, Journal of Guidance, Control, and Dynamics, 22, 4, 589-594.
 
13.
Yanushevsky R., 2007, Modern Missile Guidance, 1st Edition, CRC Press, New York.
 
14.
Zarchan P., 2012, Tactical and Strategic Missile Guidance, 6th Edition, AIAA, Reston.
 
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