Design of Sliding Model Variable Structure Guidance Law with Terminal Impact Angle Constraints

FU Zhumu; CAO Jing; WANG Xiaohong

doi:10.13976/j.cnki.xk.2015.0291

Volume 44 Issue 3

Jun. 2015

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INFORMATION AND CONTROL > 2015 > 44(3): 291-297,302. > DOI: 10.13976/j.cnki.xk.2015.0291 CSTR: 32166.14.xk.2015.0291

FU Zhumu, CAO Jing, WANG Xiaohong. Design of Sliding Model Variable Structure Guidance Law with Terminal Impact Angle Constraints[J]. INFORMATION AND CONTROL, 2015, 44(3): 291-297,302. DOI: 10.13976/j.cnki.xk.2015.0291

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Design of Sliding Model Variable Structure Guidance Law with Terminal Impact Angle Constraints

1.
Information Engineering College, Henan University of Science and Technology, Luoyang 471023, China
2.
School of Control Science and Engineering, Shandong University, Jinan 250061, China

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Received Date: August 11, 2014
Revised Date: March 05, 2015
Published Date: June 19, 2015

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Abstract

Abstract

To improve guidance precision and to ensure the ideal damage effect, an approximate vertical diving attacking guidance law of air-to-ground weapons is proposed. Based on the relative motion model for a missile and target in a two-dimensional plane, the impact angle constraints are transformed to control the terminal line of sight. According to final the position and the impact angle constraints, a sliding model variable structure guidance law that includes four guidance parameters is designed： the angle error parameter, the switching parameter, the reaching law parameter, and the constant parameter. The basis for the parameters selection is obtained by analyzing the influence of four guidance law parameters on guidance performance. The simulation is demonstrated for the designed guidance law to obtain a near zero miss distance and a 90° impact angle. The miss distance is decreased by 87.43% and the impact angle is increased by 47.01% in comparison with the proportional guidance law.
- air-to-ground missile,
- impact angle constraint,
- sliding mode variable structure,
- guidance law

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