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Technical Brief

Application of Finite-Time Integral Sliding Mode to Guidance Law Design

[+] Author and Article Information
Mehdi Golestani

Department of Electrical Engineering,
Malek-Ashtar University of Technology,
Tehran 1774-15875, Iran
e-mail: m.golestani@qiau.ac.ir

Iman Mohammadzaman

Assistant Professor
Department of Electrical Engineering,
Malek-Ashtar University of Technology,
Tehran 1774-15875, Iran
e-mail: mohammadzaman@mut.ac.ir

Mohammad Javad Yazdanpanah

Professor
School of Electrical and Computer Engineering,
University of Tehran,
Tehran 14395/515, Iran
e-mail: yazdan@ut.ac.ir

Ahmad Reza Vali

Associate Professor
Department of Electrical Engineering,
Malek-Ashtar University of Technology,
Tehran 1774-15875, Iran
e-mail: ar.vali@aut.ac.ir

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received March 12, 2014; final manuscript received June 25, 2015; published online August 13, 2015. Assoc. Editor: Heikki Handroos.

J. Dyn. Sys., Meas., Control 137(11), 114501 (Aug 13, 2015) (4 pages) Paper No: DS-14-1113; doi: 10.1115/1.4030951 History: Received March 12, 2014

In this work, a new nonlinear guidance law with finite-time convergence considering control loop dynamics is developed to intercept highly maneuvering targets. The approach is based on integral sliding mode combined with finite-time state feedback control. Since terminal guidance process occurs in a short time, the line-of-sight (LOS) angular rate should converge to zero in a finite time. The proposed guidance scheme successively guides the LOS angular rate to converge to zero in a finite-time, and stability and robustness of the new guidance law are demonstrated by means of Lyapunov stability theorem. Three-dimensional simulation results demonstrate the performance of the proposed design procedure.

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References

Figures

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Fig. 1

Planar interception geometry

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Fig. 4

The LOS angular rate in azimuth loop

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Fig. 2

Three-dimensional (3D) interceptor–target geometry

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Fig. 5

The LOS angular rate in elevation loop

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Fig. 6

The acceleration command in azimuth loop

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Fig. 7

The acceleration command in elevation loop

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