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Research Papers

Finite Time Convergence Guidance Law Accounting for Missile Autopilot

[+] Author and Article Information
Pingping Qu

The School of Electronics and
Information Engineering,
Shenyang Aerospace University,
Shenyang 110136, China;
Department of Control Science and Engineering,
Harbin Institute of Technology,
Harbin 150001, China
e-mail: qupingping_79@163.com

Chuntao Shao

Department of Control Science and Engineering,
Harbin Institute of Technology at Weihai,
Weihai 264209, China
e-mail: shaw@hitwh.edu.cn

Di Zhou

Department of Control Science and Engineering,
Harbin Institute of Technology,
Harbin 150001, China
e-mail: zhoud@hit.edu.cn

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received June 16, 2013; final manuscript received November 20, 2014; published online January 27, 2015. Assoc. Editor: May-Win L. Thein.

J. Dyn. Sys., Meas., Control 137(5), 051014 (May 01, 2015) (8 pages) Paper No: DS-13-1232; doi: 10.1115/1.4029241 History: Received June 16, 2013; Revised November 20, 2014; Online January 27, 2015

A guidance law with finite time convergence is designed using the sliding mode control method and finite time convergence control theory, accounting for the missile autopilot as second-order dynamics. The high-order derivatives of the line of sight (LOS) angle are avoided in the expression of guidance law such that it can be implemented in practical applications. The designed guidance law is effective in compensating the bad influence of the autopilot dynamics on guidance accuracy. In simulations of intercepting a non maneuvering target or a maneuvering target, respectively, the designed guidance law is compared with the adaptive sliding mode guidance (ASMG) law in the presence of missile autopilot lag. Simulation results show that the designed guidance law is able to guide a missile to accurately intercept a nonmaneuvering target or a maneuvering target with finite time, even if it escapes in a great and fast maneuver and the autopilot has a relatively large lag.

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References

Figures

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Fig. 1

Planar relative motion of missile and target

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Fig. 2

Simulation results for case 1: (a) LOS angular rate and (b) acceleration command

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Fig. 3

Simulation results for case 2: (a) LOS angular rate and (b) acceleration command

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Fig. 4

Simulation results for case 3: (a) LOS angular rate and (b) acceleration command

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Fig. 5

Simulation results for case 4: (a) LOS angular rate and (b) acceleration command

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Fig. 6

Simulation results for case 5: (a) LOS angular rate and (b) acceleration command

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Fig. 7

Simulation results for case 6: (a) LOS angular rate and (b) acceleration command

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Fig. 8

Simulation results for case 7: (a) LOS angular rate and (b) acceleration command

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Fig. 9

Simulation results for case 8: (a) LOS angular rate and (b) acceleration command

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Fig. 10

Simulation results for case 9: (a) LOS angular rate and (b) acceleration command

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