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Three-dimensional Adaptive Sliding Mode Guidance Law for Missile with Autopilot Lag and Actuator Fault

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  • Control Theory and Applications
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Abstract

This paper investigates guidance scheme for missile with actuator failure and dynamics of autopilot. Firstly, considering first-order dynamics of autopilot, the guidance model with actuator failure is established. Secondly, an adaptive sliding mode fault-tolerant guidance law is designed on the basis of passive fault-tolerant technique and a novel nonsingular fast terminal sliding mode (NFTSM) manifold. Then, the adaptive algorithm with the feature of low-pass filter is proposed to ensure that adaptive parameters are bounded when the sliding mode is non-ideal. Finally, Lyapunov stability theory is adopted to prove that the states of closed-loop system are practical finite-time stability. Simulation results demonstrate the effectiveness and robustness of the proposed guidance strategy under the certain actuator failure.

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Authors and Affiliations

  1. School of Mechanical and Electrical Engineering, Heilongjiang University, Heilongjiang, China

    Guiying Li & Zhongxian Wang

  2. School of Electrical Engineering, Heilongjiang University, Heilongjiang, China

    Zhigang Yu

Authors
  1. Guiying Li
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  2. Zhigang Yu
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  3. Zhongxian Wang
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Corresponding author

Correspondence to Zhigang Yu.

Additional information

Recommended by Associate Editor Chang Kyung Ryoo under the direction of Editor Duk-Sun Shim. This work was supported by Natural Science Foundation of Heilongjiang Province of China (Grant No. F2018024) and Fundamental Research Fund for Heilongjiang Provincial Universities of China (Grant No. HDJCCX-201622).

Guiying Li received her B.Sc. degree from the Harbin Institute of Technology, Harbin, China, in 1999, and her M.Sc. degree form Northeast Forest University in 2006. Since 2006, she has been with School of Mechanical and Electrical Engineering, Heilongjiang University, where she is currently an Electrical Engineer. Her main research interests include guidance and control, intelligent control, and system identification.

Zhigang Yu received his M.Sc. degree in Control Theory and control Engineering form Northeast Forest University, Harbin, China, in 2003, and his Ph.D. degree in Control Science and Engineering from the Harbin Institute of Technology, Harbin, China, in 2007. Since 2007, he has been with School of Electrical Engineering, Heilongjiang University, where he is currently an Associate Professor. His main research interests include nonlinear system robust control, and intelligent control.

Zhongxian Wang was born in Heilongjiang Province, China, in 1982. He received his B.S. degree in electrical engineering from Harbin University of Science and Technology, Harbin, China, in 2004, and his M.S. degree in control and instrument engineering from Wonkwang University, Iksan, Korea, in 2007. He is currently a Senior Engineer in the School of Mechanical and Electrical Engineering at Heilongjiang University, Harbin, China. His research interests include high-frequency power conversion technique.

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Li, G., Yu, Z. & Wang, Z. Three-dimensional Adaptive Sliding Mode Guidance Law for Missile with Autopilot Lag and Actuator Fault. Int. J. Control Autom. Syst. 17, 1369–1377 (2019). https://doi.org/10.1007/s12555-017-0731-9

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  • DOI: https://doi.org/10.1007/s12555-017-0731-9

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