JOURNAL ARTICLE

3-D Impact Time and Angle Control Guidance Law Based on Sliding Mode without Speed Control.

  • Published In: Journal of Circuits, Systems & Computers, 2024, v. 33, n. 11. P. 1 1 of 3

  • Database: Academic Search Ultimate 2 of 3

  • Authored By: Zhang, Zhongqiu; You, Jun; Han, Zhiguo 3 of 3

Abstract

In modern warship, coordinated combat strategies require missiles hit targets simultaneously, sometimes even require angle constraints, which is difficult to replicate in three-dimensional (3-D) models. This paper proposes a novel 3-D sliding mode guidance law with multiple constraints. First, the 3-D no-thrust guidance model is derived in the coordinate system with Y -axis upward. Second, a novel guidance strategy is proposed. In pitch direction, a fast nonsingular sliding mode surface algorithm is proposed to satisfy the desired line-of-sight elevation angle. In yaw direction, based on the guidance conditions, a special sliding mode surface is proposed, which can achieve desired line-of-sight azimuth angle and desired impact time when reaching the sliding surface. Finally, simulations and comparisons verify the good performance. [ABSTRACT FROM AUTHOR]

Additional Information

  • Source:Journal of Circuits, Systems & Computers. 2024/07, Vol. 33, Issue 11, p1
  • Document Type:Article
  • Subject Area:History
  • Publication Date:2024
  • ISSN:0218-1266
  • DOI:10.1142/S0218126624501184
  • Accession Number:178439740
  • Copyright Statement:Copyright of Journal of Circuits, Systems & Computers is the property of World Scientific Publishing Company and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

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