Integral Global Sliding Mode Guidance for Impact Angle Control

Shaoming He; Defu Lin; Jiang Wang

doi:10.1109/TAES.2018.2876588

Integral Global Sliding Mode Guidance for Impact Angle Control

Shaoming He, Defu Lin, Jiang Wang^*

^*此作品的通讯作者

宇航学院

Cranfield University

科研成果: 期刊稿件 › 文章 › 同行评审

40 引用（Scopus）

摘要

This paper proposes a new guidance law based on integral sliding mode control (ISMC) technique for maneuvering target interception with impact angle constraint. A time-varying function weighted line-of-sight error dynamics, representing the nominal guidance performance, is introduced first. The proposed guidance law is derived by utilizing ISMC to follow the desired error dynamics. The convergence of the guidance law developed is supported by Lyapunov stability. Simulations with extensive comparisons explicitly demonstrate the effectiveness of the proposed approach.

源语言	英语
页（从-至）	1843-1849
页数	7
期刊	IEEE Transactions on Aerospace and Electronic Systems
卷	55
期	4
DOI	https://doi.org/10.1109/TAES.2018.2876588
出版状态	已出版 - 1 8月 2019

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10.1109/TAES.2018.2876588

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He, S., Lin, D., & Wang, J. (2019). Integral Global Sliding Mode Guidance for Impact Angle Control. IEEE Transactions on Aerospace and Electronic Systems, 55(4), 1843-1849. https://doi.org/10.1109/TAES.2018.2876588

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abstract = "This paper proposes a new guidance law based on integral sliding mode control (ISMC) technique for maneuvering target interception with impact angle constraint. A time-varying function weighted line-of-sight error dynamics, representing the nominal guidance performance, is introduced first. The proposed guidance law is derived by utilizing ISMC to follow the desired error dynamics. The convergence of the guidance law developed is supported by Lyapunov stability. Simulations with extensive comparisons explicitly demonstrate the effectiveness of the proposed approach.",

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AB - This paper proposes a new guidance law based on integral sliding mode control (ISMC) technique for maneuvering target interception with impact angle constraint. A time-varying function weighted line-of-sight error dynamics, representing the nominal guidance performance, is introduced first. The proposed guidance law is derived by utilizing ISMC to follow the desired error dynamics. The convergence of the guidance law developed is supported by Lyapunov stability. Simulations with extensive comparisons explicitly demonstrate the effectiveness of the proposed approach.

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Integral Global Sliding Mode Guidance for Impact Angle Control

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