نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشکده مهندسی مکانیک، دانشگاه صنعتی شریف، تهران، ایران

2 دانشکده مهندسی برق، دانشگاه صنعتی خواجه نصیرالدین طوسی، تهران، ایران

10.22034/jsst.2021.1279

چکیده

در این مقاله، با استفاده از روش کنترلی پیش‌بین مدل مبنا و بر پایه استراتژی هدایت تناسبی به طراحی قانون هدایت بهینه صریح جهت هدایت موشک پدافندی به سمت هدف در حال مانور در فضای سه‌بعدی پرداخته می‌شود. این روش کنترلی با پیش‌بینی رفتار سیستم در آینده، در خلال بهینه‌سازی یک تابع هزینه مشخص قانون کنترلی بهینه را محاسبه می‌کند. رویکرد کنترلی پیش‌بین تعمیم‌یافته که در این مقاله مورد استفاده قرار گرفته است، مسأله بهینه‌سازی را به صورت برون‌خط حل می‌کند تا فرم بسته قانون کنترلی بهینه را به دست آورد. به این منظور، ابتدا معادلات حرکت مجموعه موشک و هدف در دستگاه سه‌بعدی بازنویسی می‌شود. سپس قانون کنترلی بهینه به صورت تابعی صریح از متغیرهای حالت محاسبه می‌گردد. عملکرد سیستم هدایت پیشنهادی با سیستم هدایت تناسبی APN در سه سناریو متفاوت مقایسه شده و نتایج شبیه‌سازی نشان‌دهنده کارایی مطلوب سیستم پیشنهادی به ویژه در مقابله با اهداف با تغییر مسیرهای ناگهانی می‌باشد.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Optimal Proportional Navigation in Three-Dimensional Space Using Model Predictive Control Approach

نویسندگان [English]

  • Reza Sheikhbahaei 1
  • Saeed Khankalantary 2

1 Department of Mechanical Engineering, Sharif University of Technology (SUT), Tehran, I.R.Iran

2 Department of Electrical Engineering, K. N. Toosi University of Technology, Tehran. Iran

چکیده [English]

In this study, on the basis of proportional navigation strategy, design of explicit optimal guidance law for missiles tracking maneuvering targets in three-dimensional space using model predictive control is addressed. The model predictive control employs a model to predict the future process behavior and calculates an optimal control input at each time step through the optimization of an objective function. Generalized model predictive control approach, employed in this study, solves the optimization problem offline to obtain the closed form optimal control law. In this paper, firstly, the equations describing the missile-target relative motion kinematics are formulated. Then, the optimal control law, as an explicit function of the state vector is obtained. The evaluation of the proposed scheme is studied by the comparison of the simulation results with the augmented proportional navigation system. Simulation studies, in three different scenarios, demonstrates appropriate performance for the proposed guidance system specially against maneuvering targets.

کلیدواژه‌ها [English]

  • Model predictive Control
  • Proportional navigation
  • Three dimensional
  • Explicit Optimal Guidance Law
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