کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
1717883 1520093 2015 10 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Continuous second-order sliding mode based impact angle guidance law
ترجمه فارسی عنوان
قوانین هدایت زاویه ضربه بر اساس حالت لغزش مداوم مرتبه دوم
کلمات کلیدی
حالت کشویی دوم مرتبه، حالت لغزنده ترمینال غیرمجاز، ناظر اختلال، هدایت موشکی، محدودیت زاویه ضربه، اهداف مانور
موضوعات مرتبط
مهندسی و علوم پایه سایر رشته های مهندسی مهندسی هوافضا
چکیده انگلیسی

In this paper, a new continuous robust impact angle constraint guidance law with finite-time convergence is proposed for intercepting maneuvering targets with unknown acceleration bounds. The presented guidance law is based on nonsingular terminal sliding mode (NTSM), smooth second-order sliding mode and finite-time convergence disturbance observer (FTDOB). In light of the introduced FTDOB, which is used to estimate and compensate the lumped uncertainty in missile guidance system, no prior knowledge of target maneuver is required. Thus, the proposed guidance law is capable of real implementation. Differently from the widely used boundary layer technique, chattering is eliminated effectively under the proposed guidance law without any performance sacrifice. Using finite-time bounded function approach and Lyapunov stability criteria, rigorous finite-time stability proof in both reaching and sliding phases is given. Theoretical analysis and numerical simulations show that the proposed guidance law can achieve more accurate interception with a wide range of intercept angles and superior overall performance than traditional NTSM algorithm.

ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Aerospace Science and Technology - Volume 41, February 2015, Pages 199–208
نویسندگان
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