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Differentiator-Based Incremental Three-Dimensional Terminal Angle Guidance With Enhanced Robustness.

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Title: Differentiator-Based Incremental Three-Dimensional Terminal Angle Guidance With Enhanced Robustness.
Authors: Han, Tuo1 (AUTHOR), Shin, Hyo-Sang2 (AUTHOR) h.shin@cranfield.ac.uk, Hu, Qinglei3 (AUTHOR), Tsourdos, Antonios2 (AUTHOR), Xin, Ming4 (AUTHOR)
Source: IEEE Transactions on Aerospace & Electronic Systems. Oct2022, Vol. 58 Issue 5, p4020-4032. 13p.
Subjects: Sliding mode control, Angles, Nonlinear dynamical systems
Abstract: In this article, an incremental guidancelaw with terminal angle constraint is proposed against maneuvering targets in the 3-D space. First, a sliding surface is constructed such that its first-order dynamics excludes the relative range and line-of-sight angles in the perturbation. This manipulation avoids unboundedperturbations induced by target maneuvers near collision. Then, a benchmark guidance law is derived via the nonlinear dynamic inversion (NDI) based sliding mode control (NDI-SMC). To further enhance guidance system robustness, an incremental nonlinear dynamic inversion (INDI) based SMC (INDI-SMC) 3-D guidance law is developed. The INDI-SMC guidance law exploits the first-order derivative of the sliding variable and guidance command output at the latest step, which leads to reduced perturbation and thus requires smaller gains than the NDI-SMC guidance law. A multivariable continuous differentiator is employed to estimate the sliding variable's first-order derivative for guidance law implementation. Moreover, the stability of the differentiator is analyzed and the guidance robustness under uncertainties is compared. Extensive numerical simulations and a Monte Carlo test are conducted to verify effectiveness and robustness of the proposed method. [ABSTRACT FROM AUTHOR]
Copyright of IEEE Transactions on Aerospace & Electronic Systems is the property of IEEE 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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  Data: Differentiator-Based Incremental Three-Dimensional Terminal Angle Guidance With Enhanced Robustness.
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  Data: <searchLink fieldCode="JN" term="%22IEEE+Transactions+on+Aerospace+%26+Electronic+Systems%22">IEEE Transactions on Aerospace & Electronic Systems</searchLink>. Oct2022, Vol. 58 Issue 5, p4020-4032. 13p.
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  Data: <searchLink fieldCode="DE" term="%22Sliding+mode+control%22">Sliding mode control</searchLink><br /><searchLink fieldCode="DE" term="%22Angles%22">Angles</searchLink><br /><searchLink fieldCode="DE" term="%22Nonlinear+dynamical+systems%22">Nonlinear dynamical systems</searchLink>
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  Label: Abstract
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  Data: In this article, an incremental guidancelaw with terminal angle constraint is proposed against maneuvering targets in the 3-D space. First, a sliding surface is constructed such that its first-order dynamics excludes the relative range and line-of-sight angles in the perturbation. This manipulation avoids unboundedperturbations induced by target maneuvers near collision. Then, a benchmark guidance law is derived via the nonlinear dynamic inversion (NDI) based sliding mode control (NDI-SMC). To further enhance guidance system robustness, an incremental nonlinear dynamic inversion (INDI) based SMC (INDI-SMC) 3-D guidance law is developed. The INDI-SMC guidance law exploits the first-order derivative of the sliding variable and guidance command output at the latest step, which leads to reduced perturbation and thus requires smaller gains than the NDI-SMC guidance law. A multivariable continuous differentiator is employed to estimate the sliding variable's first-order derivative for guidance law implementation. Moreover, the stability of the differentiator is analyzed and the guidance robustness under uncertainties is compared. Extensive numerical simulations and a Monte Carlo test are conducted to verify effectiveness and robustness of the proposed method. [ABSTRACT FROM AUTHOR]
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  Data: <i>Copyright of IEEE Transactions on Aerospace & Electronic Systems is the property of IEEE 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.</i> (Copyright applies to all Abstracts.)
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        Value: 10.1109/TAES.2022.3158639
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      – Code: eng
        Text: English
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        PageCount: 13
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      – SubjectFull: Sliding mode control
        Type: general
      – SubjectFull: Angles
        Type: general
      – SubjectFull: Nonlinear dynamical systems
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            NameFull: Han, Tuo
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            NameFull: Hu, Qinglei
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            NameFull: Xin, Ming
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            – D: 01
              M: 10
              Text: Oct2022
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              Y: 2022
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