Sliding mode control based impact angle control guidance considering the seeker?s field-of-view constraint |
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Affiliation: | 1. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics & Astronautics, Beijing 100191, China;2. Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics & Astronautics, Beijing 100191, China;3. Beijing Institute of Space Launch Technology, Beijing 100076, China;1. School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China;2. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;1. School of Automation, Beijing Institute of Technology, Beijing 100081, China;2. Key Laboratory for Intelligent Control & Decision of Complex Systems, Beijing Institute of Technology, Beijing 100081, China |
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Abstract: | The problem of impact angle control guidance for a field-of-view constrained missile against non-maneuvering or maneuvering targets is solved by using the sliding mode control theory. The existing impact angle control guidance laws with field-of-view constraint are only applicable against stationary targets and most of them suffer abrupt-jumping of guidance command due to the application of additional guidance mode switching logic. In this paper, the field-of-view constraint is handled without using any additional switching logic. In particular, a novel time-varying sliding surface is first designed to achieve zero miss distance and zero impact angle error without violating the field-of-view constraint during the sliding mode phase. Then a control integral barrier Lyapunov function is used to design the reaching law so that the sliding mode can be reached within finite time and the field-of-view constraint is not violated during the reaching phase as well. A nonlinear extended state observer is constructed to estimate the disturbance caused by unknown target maneuver, and the undesirable chattering is alleviated effectively by using the estimation as a compensation item in the guidance law. The performance of the proposed guidance law is illustrated with simulations. |
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Keywords: | Guidance Sliding mode control Impact angle control Field-of-view constraint Integral barrier Lyapunov function Nonlinear extended state observer |
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