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Research Papers

A Guidance Law With Terminal Impact Angle Constraint Accounting for Missile Autopilot

[+] Author and Article Information
Di Zhou

Department of Control Science and Engineering,
Harbin Institute of Technology,
Mailbox 327,
Harbin 150001, China
e-mail: zhoud@hit.edu.cn

Pingping Qu

Department of Control Science and Engineering,
Harbin Institute of Technology,
Mailbox 327,
Harbin 150001, China;
The School of Electronics
and Information Engineering,
Shenyang Aerospace University,
Shenyang 110136, China

Sheng Sun

Department of Control Science and Engineering,
Harbin Institute of Technology,
Mailbox 327,
Harbin 150001, China

Contributed by the Dynamic Systems Division of ASME for publication in the Journal of Dynamic Systems, Measurement, and Control. Manuscript received May 18, 2012; final manuscript received March 29, 2013; published online June 6, 2013. Assoc. Editor: Yang Shi.

J. Dyn. Sys., Meas., Control 135(5), 051009 (Jun 06, 2013) (10 pages) Paper No: DS-12-1144; doi: 10.1115/1.4024202 History: Received May 18, 2012; Revised March 29, 2013

A sliding-mode guidance (SMG) law is designed to intercept maneuvering targets with impact angle constrained flight trajectories under the assumption of ideal missile autopilot. Furthermore, accounting for the autopilot as second-order dynamics, a new guidance law with terminal impact angle constraint is designed using the dynamic surface control method. Some first-order low-pass filters are introduced into the designing process to avoid the occurrence of high-order derivatives of the line of sight (LOS) angle in the expression of the guidance law such that the guidance law can be implemented in practical applications. The proposed guidance law is effective in compensating for the second-order autopilot lag. Simulation results show that it is able to guide a missile to impact a maneuvering target with a desired angle and a small miss distance.

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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 in the elevation loop for case 1

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Fig. 3

Simulation results in the elevation loop for case 2

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Fig. 4

Simulation results for case 3 in the elevation loop

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Fig. 5

Simulation results for case 3 in the azimuth loop

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