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
Submission date: 2018-06-25
Acceptance date: 2019-08-26
Online publication date: 2020-01-15
Publication date: 2020-01-15
Journal of Theoretical and Applied Mechanics 2020;58(1):169-182
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.
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