Volume 14, Issue 3 (September 2018)                   IJEEE 2018, 14(3): 204-212 | Back to browse issues page

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Behnamgol V, Vali A R, Mohammadi A. Design a Guidance Law Considering Approximation of Missile Control Loop Dynamics Using Adaptive Back-Stepping Theory. IJEEE 2018; 14 (3) :204-212
URL: http://ijeee.iust.ac.ir/article-1-1068-en.html
Design a Guidance Law Considering Approximation of Missile Control Loop Dynamics Using Adaptive Back-Stepping Theory
V. Behnamgol , A. R. Vali , A. Mohammadi
Abstract:   (4431 Views)
In this paper, a new guidance law is designed to improve the performance of a homing missiles guidance system in terminal phase. For this purpose first of all, the two dimensions equations of motion are formulated, then the approximation dynamic of missile control loop is added to these equations which are nonlinear whit unmatched uncertainty. Then, a new adaptive back-stepping method is developed in order to control this system. An adaptive term is used in the control law that is converged to the uncertainty. This convergence is proved based on Lyapunov stability theorem. Therefore using this adaptive term in the control law can be eliminated the uncertainty. Based on this algorithm, a new guidance law is designed. Then its performance is compared with common guidance laws in a guidance loop simulation in the presence of control loop dynamics.
Keywords: Guidance Law , Control Loop Dynamics , Adaptive Back-Stepping Control , Unmatched Uncertainty
Full-Text [PDF 861 kb]   (2425 Downloads)    
Type of Study: Research Paper | Subject: Nonlinear Control Systems
Received: 2017/03/25 | Revised: 2018/10/19 | Accepted: 2018/02/28
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© 2022 by the authors. Licensee IUST, Tehran, Iran. This is an open access journal distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial 4.0 International (CC BY-NC 4.0) license.