Three-dimensional optimal sliding mode guidance with impact angle constraint

Zhe Chen; Shengjing Tang; Jie Guo

doi:10.1109/WCICA.2014.7053392

Three-dimensional optimal sliding mode guidance with impact angle constraint

Zhe Chen, Shengjing Tang, Jie Guo

School of Aerospace Engineering

Beijing Institute of Technology

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

4 Citations (Scopus)

Abstract

For issues that external uncertain disturbances and parameters perturbation can result in low guidance accuracy as well as poor robustness in traditional terminal phase, an optimal sliding mode guidance law with impact angle constraint was proposed. Firstly three-dimensional mathematical model of missile-target relative motion was established based on point mass assumption, then linear quadratic regulator with differential Riccati equations was adopted to meet the terminal impact angle while sliding mode control used to augment guidance robustness. The proof of Lyapunov stability and simulation results show that the combined three-dimensional optimal sliding mode guidance law can satisfy desired performance index and ensure high accuracy as well as strong robustness.

Original language	English
Title of host publication	Proceeding of the 11th World Congress on Intelligent Control and Automation, WCICA 2014
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	4045-4049
Number of pages	5
Edition	March
ISBN (Electronic)	9781479958252
DOIs	https://doi.org/10.1109/WCICA.2014.7053392
Publication status	Published - 2 Mar 2015
Event	2014 11th World Congress on Intelligent Control and Automation, WCICA 2014 - Shenyang, China Duration: 29 Jun 2014 → 4 Jul 2014

Publication series

Name	Proceedings of the World Congress on Intelligent Control and Automation (WCICA)
Number	March
Volume	2015-March

Conference

Conference	2014 11th World Congress on Intelligent Control and Automation, WCICA 2014
Country/Territory	China
City	Shenyang
Period	29/06/14 → 4/07/14

Keywords

Impact angle constraint
Optimal control
Sliding mode guidance
Three-dimensional guidance

Access to Document

10.1109/WCICA.2014.7053392

Cite this

Chen, Z., Tang, S., & Guo, J. (2015). Three-dimensional optimal sliding mode guidance with impact angle constraint. In Proceeding of the 11th World Congress on Intelligent Control and Automation, WCICA 2014 (March ed., pp. 4045-4049). Article 7053392 (Proceedings of the World Congress on Intelligent Control and Automation (WCICA); Vol. 2015-March, No. March). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/WCICA.2014.7053392

Chen, Zhe ; Tang, Shengjing ; Guo, Jie. / Three-dimensional optimal sliding mode guidance with impact angle constraint. Proceeding of the 11th World Congress on Intelligent Control and Automation, WCICA 2014. March. ed. Institute of Electrical and Electronics Engineers Inc., 2015. pp. 4045-4049 (Proceedings of the World Congress on Intelligent Control and Automation (WCICA); March).

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title = "Three-dimensional optimal sliding mode guidance with impact angle constraint",

abstract = "For issues that external uncertain disturbances and parameters perturbation can result in low guidance accuracy as well as poor robustness in traditional terminal phase, an optimal sliding mode guidance law with impact angle constraint was proposed. Firstly three-dimensional mathematical model of missile-target relative motion was established based on point mass assumption, then linear quadratic regulator with differential Riccati equations was adopted to meet the terminal impact angle while sliding mode control used to augment guidance robustness. The proof of Lyapunov stability and simulation results show that the combined three-dimensional optimal sliding mode guidance law can satisfy desired performance index and ensure high accuracy as well as strong robustness.",

keywords = "Impact angle constraint, Optimal control, Sliding mode guidance, Three-dimensional guidance",

author = "Zhe Chen and Shengjing Tang and Jie Guo",

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Chen, Z, Tang, S & Guo, J 2015, Three-dimensional optimal sliding mode guidance with impact angle constraint. in Proceeding of the 11th World Congress on Intelligent Control and Automation, WCICA 2014. March edn, 7053392, Proceedings of the World Congress on Intelligent Control and Automation (WCICA), no. March, vol. 2015-March, Institute of Electrical and Electronics Engineers Inc., pp. 4045-4049, 2014 11th World Congress on Intelligent Control and Automation, WCICA 2014, Shenyang, China, 29/06/14. https://doi.org/10.1109/WCICA.2014.7053392

Three-dimensional optimal sliding mode guidance with impact angle constraint. / Chen, Zhe; Tang, Shengjing; Guo, Jie.
Proceeding of the 11th World Congress on Intelligent Control and Automation, WCICA 2014. March. ed. Institute of Electrical and Electronics Engineers Inc., 2015. p. 4045-4049 7053392 (Proceedings of the World Congress on Intelligent Control and Automation (WCICA); Vol. 2015-March, No. March).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

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N2 - For issues that external uncertain disturbances and parameters perturbation can result in low guidance accuracy as well as poor robustness in traditional terminal phase, an optimal sliding mode guidance law with impact angle constraint was proposed. Firstly three-dimensional mathematical model of missile-target relative motion was established based on point mass assumption, then linear quadratic regulator with differential Riccati equations was adopted to meet the terminal impact angle while sliding mode control used to augment guidance robustness. The proof of Lyapunov stability and simulation results show that the combined three-dimensional optimal sliding mode guidance law can satisfy desired performance index and ensure high accuracy as well as strong robustness.

AB - For issues that external uncertain disturbances and parameters perturbation can result in low guidance accuracy as well as poor robustness in traditional terminal phase, an optimal sliding mode guidance law with impact angle constraint was proposed. Firstly three-dimensional mathematical model of missile-target relative motion was established based on point mass assumption, then linear quadratic regulator with differential Riccati equations was adopted to meet the terminal impact angle while sliding mode control used to augment guidance robustness. The proof of Lyapunov stability and simulation results show that the combined three-dimensional optimal sliding mode guidance law can satisfy desired performance index and ensure high accuracy as well as strong robustness.

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Chen Z, Tang S, Guo J. Three-dimensional optimal sliding mode guidance with impact angle constraint. In Proceeding of the 11th World Congress on Intelligent Control and Automation, WCICA 2014. March ed. Institute of Electrical and Electronics Engineers Inc. 2015. p. 4045-4049. 7053392. (Proceedings of the World Congress on Intelligent Control and Automation (WCICA); March). doi: 10.1109/WCICA.2014.7053392

Three-dimensional optimal sliding mode guidance with impact angle constraint

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