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Research Papers

Three-Dimensional Impact Angle Guidance Laws Based on Model Predictive Control and Sliding Mode Disturbance Observer

[+] Author and Article Information
Shaoming He

School of Aerospace Engineering,
Beijing Institute of Technology,
Beijing 100081, China
e-mail: shaoming.he.cn@gmail.com

Wei Wang

School of Aerospace Engineering,
Beijing Institute of Technology,
Beijing 100081, China
e-mail: wangweiyh1@163.com

Jiang Wang

School of Aerospace Engineering,
Beijing Institute of Technology,
Beijing 100081, China
e-mail: wjbest2003@163.com

1Corresponding author.

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received July 16, 2015; final manuscript received March 23, 2016; published online May 25, 2016. Assoc. Editor: Yongchun Fang.

J. Dyn. Sys., Meas., Control 138(8), 081006 (May 25, 2016) (11 pages) Paper No: DS-15-1318; doi: 10.1115/1.4033272 History: Received July 16, 2015; Revised March 23, 2016

This paper presents a suboptimal three-dimensional guidance law to intercept unknown maneuvering targets with terminal angle constraint using multivariable control design. The presented guidance law is essentially a composite control method, which is constructed through a combination of standard continuous model predictive control (MPC) and adaptive multivariable sliding mode disturbance observer (SMDO). More specifically, the MPC method is utilized to obtain optimal line-of-sight (LOS) angle tracking performance for nonmaneuvering targets, while the SMDO technique is used to estimate and compensate for the unknown target maneuver online. By virtue of the adaptive nature, the proposed guidance law does not require any information on the bounds of target maneuver and its gradient except for their existence. The stability of the closed-loop guidance system is also analyzed by using Lyapunov function method. Simulation results clearly confirm the effectiveness of the proposed formulation against a maneuvering target.

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Figures

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Fig. 1

Three-dimensional homing engagement geometry

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Fig. 2

Simulation results for case 1: (a) LOS angular rate in elevation, (b) LOS angular rate in azimuth, (c) LOS angle in elevation, and (d) LOS angle in azimuth

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Fig. 3

Simulation results for case 1: (a) missile acceleration in elevation, (b) missile acceleration in azimuth, (c) SMDO estimation performance, and (d) adaptive parameter

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Fig. 4

Simulation results for case 2: (a) LOS angular rate in elevation, (b) LOS angular rate in azimuth, (c) LOS angle in elevation, (d) LOS angle in azimuth, (e) missile acceleration in elevation, and (f) missile acceleration in azimuth

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Fig. 5

Simulation results for case 3: (a) LOS angular rate in elevation, (b) LOS angular rate in azimuth, (c) LOS angle in elevation, (d) LOS angle in azimuth, (e) missile acceleration in elevation, and (f) missile acceleration in azimuth

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Fig. 6

Disturbance estimation performance under different k: (a) SMDO estimation performance and (b) adaptive parameter

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Fig. 7

Disturbance estimation performance under different ci: (a) SMDO estimation performance and (b) adaptive parameter

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