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در این مقاله، بهینه‌سازی افق محدود ارتفاع مداری یک ماهواره‌بر بر اساس کنترل افق محدود غیرخطی ارایه شده است. رویکرد روش پیشنهادی، بهینه‌سازی متغیرهای مسیر پرواز نظیر پارامترهای زاویه حمله و همچنین بهینه‌سازی تراست مراحل برای دست‌یابی به حداکثر ارتفاع مداری است. در این روش، ابتدا مسیر نامی حامل فضایی با بهره‌گیری از روش‌های مختلف بهینه‌سازی نظیر جستجوی الگو، برنامه‌ریزی مربعی متوالی و الگوریتم ژنتیک بدست آمده و با یکدیگر مقایسه شده است. مسیر حاصله، بر اساس شرایط نامی حامل فضایی و با بهینه‌سازی متغیرهای تابع زاویه حمله حاصل شده است. در این روش، با استفاده از روش بهینه‌سازی افق محدود، تراست بهینه در مراحل مختلف با فرض ثابت بودن ضربه کل هر یک از مراحل بدست آمده و ارتفاع مداری بیشینه شده است. انعطاف پذیری این روش در حل مسائل بهینه‌سازی و امکان در نظر گرفتن قیود مختلف مسیر پرواز، از مزایای این روش پیشنهادی افق محدود است. الگوریتم پیشنهادی در بهینه‌سازی ارتفاع مداری یک حامل فضایی بومی بکار رفته و نتایج شبیه‌سازی‌ بیانگر افزایش 24 کیلومتری ارتفاع مداری آن نسبت به شرایط مسیر نامی آن است.
Orbital Optimization of A Satellite Launch Vehicle With A Nonlinear Receding Horizon Control
1 Electrical and Control Engineering Department, Malek Ashtar University of Technology
In this paper, the finite horizon orbital optimization of a satellite launch vehicle based on nonlinear predictive model is presented. The proposed method optimizes the flight path variables such as the angle of attack parameters as well as the optimization of the trust value of each stage to achieve the maximum orbital altitude. In this method, the nominal path of the space carrier is obtained and compared with different optimization methods such as pattern search, sequential square programming and genetic algorithm. The resulting path is obtained based on the nominal conditions of the space carrier and by optimizing the variables of the angle of attack function. In this method, using the finite horizon optimization method, the optimal trust in each stage is accomplished with assuming that the total specific impact of each stage is constant. The flexibility of this method in solving optimization problems and the possibility of considering different flight path constraints are some of the advantages of this proposed limited horizon method. The proposed algorithm is used to optimize the orbital height of a native space carrier, and the simulation results show a 24 km increase in its orbital height relative to its nominal path conditions.
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دوره 10، شماره 2 - شماره پیاپی 2
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مهدی آبادی, مهران, & قهرمانی, نعمت اله. (1400). بهینه‌سازی ارتفاع مداری یک ماهواره‌بر با بهره‌گیری از کنترل افق محدود غیرخطی. دانش و فناوری هوافضا, 10(2), 145-155.
مهران مهدی آبادی; نعمت اله قهرمانی. "بهینه‌سازی ارتفاع مداری یک ماهواره‌بر با بهره‌گیری از کنترل افق محدود غیرخطی". دانش و فناوری هوافضا, 10, 2, 1400, 145-155.
مهدی آبادی, مهران, قهرمانی, نعمت اله. (1400). 'بهینه‌سازی ارتفاع مداری یک ماهواره‌بر با بهره‌گیری از کنترل افق محدود غیرخطی', دانش و فناوری هوافضا, 10(2), pp. 145-155.
مهدی آبادی, مهران, قهرمانی, نعمت اله. بهینه‌سازی ارتفاع مداری یک ماهواره‌بر با بهره‌گیری از کنترل افق محدود غیرخطی. دانش و فناوری هوافضا, 1400; 10(2): 145-155.