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 |
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页(从-至) | 1843-1849 |
页数 | 7 |
期刊 | IEEE Transactions on Aerospace and Electronic Systems |
卷 | 55 |
期 | 4 |
DOI | |
出版状态 | 已出版 - 1 8月 2019 |