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Iranian Journal of Electrical and Electronic Engineering، جلد ۱۴، شماره ۳، صفحات ۲۰۴-۲۱۲
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چکیده فارسی مقاله
کلیدواژه‌های فارسی مقاله
عنوان انگلیسی Design a Guidance Law Considering Approximation of Missile Control Loop Dynamics Using Adaptive Back-Stepping Theory
چکیده انگلیسی مقاله 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.
کلیدواژه‌های انگلیسی مقاله
نویسندگان مقاله | V. Behnamgol
Department of Control Engineering, Malek Ashtar University of Technology, Tehran, Iran.


| A. R. Vali
Department of Control Engineering, Malek Ashtar University of Technology, Tehran, Iran.


| A. Mohammadi
Department of Control Engineering, Malek Ashtar University of Technology, Tehran, Iran.
نشانی اینترنتی http://ijeee.iust.ac.ir/browse.php?a_code=A-10-1112-2&slc_lang=en&sid=1
فایل مقاله اشکال در دسترسی به فایل - ./files/site1/rds_journals/446/article-446-832709.pdf
کد مقاله (doi)
زبان مقاله منتشر شده en
موضوعات مقاله منتشر شده 3-Nonlinear Control Systems
نوع مقاله منتشر شده Research Paper
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