نویسندگان

دانشگاه خواجه نصیر الدین طوسی - هوافضا

چکیده

یکی از مهم‌ترین مسائلی که در حال حاضر در سطح محافل هوافضایی مطرح است و در کشور ما نیز از موضوعات به‌روز است، بحث بهینه سازی طراحـی اجسام پرنـده است. از آنجا که اجسام پـرنـده و به‌طـور مثال ماهواره‌بـرهایی که مـورد بحـث ایـن پژوهش هستند، از چندین زیرسیستم با تأثیر متقابل بر یکدیگر تشکیل شده‌اند، برای انجام بهینه‌سازی طراحی آنها از ساختار‌های مختلف بهینه‌سازی طراحی چندموضوعی (MDO)، استفاده می‌شود. در استفاده از روش‌های چند موضوعی برای بهینه‌سازی موضوعات کاری مختلف یکی از مسائل مهم که بسیار تأثیـر گـذار است، انتخاب الگوریتم بهینه‌سازی مناسب است. در این پژوهش، الگوریتم طراحی ماهواره‌بر سبک سوخت مایع در فاز طراحی مفهومی به روش همه در یک مرتبه (AAO)، با درنظرگرفتن چهار موضوع سازه، آیرودینامیک، مسیر پرواز و پیشرانش با هدف کمینه‌سازی جرم لحظة‌ برخاست مدل‌سازی شــده و عملکــرد الگوریتم‌های بهینـه‌سازی گرادیانـی (SQP)، و تکاملی (GA)، بر روی آن از نظر سرعت رسیدن به جواب با حل یک مسئله طراحی مورد بررسی قرار گرفته است و نتایج با روش طراحی سنتی (روش طراحی آماری) مورد مقایسه واقع شده است و نشان داده شده است که چنانچه از جواب طراحی آماری به‌عنوان نقطة شروع در بهینه‌سازی با الگوریتم گرادیانی استفاده شود، می‌توان به بهینه سراسری رسید.

کلیدواژه‌ها

عنوان مقاله [English]

Comparison Between Traditional Method (Statistical Method) and Multidisciplinary Optimization Method (AAO) in Designing of a Lightweight Liquid Propellant LV

نویسندگان [English]

  • S. M. Hashemi Doulabi
  • H. Darabi
  • J. Roshnian

چکیده [English]

One of the most important problems that nowadays are common in aerospace societies in Iran and also around the world is how to optimize the designing of the flight objects. Since the flight objects like LVs, which are the subject of this paper, are composed of several subsystems that have influences to each others, the multidisciplinary design optimization methods(MDO) are commonly used for doing design optimization of them. In usage of the multidisciplinary design optimization methods for different objects, to select the proper optimization algorithm is one of the very important problems. In this research the conceptual design of a lightweight liquid propellant LV is done with the all at once (AAO) method. The object of optimization is to minimize gross launch weight and four disciplines of structure, aerodynamics, trajectory, and propulsion are considered. Performance of gradient based algorithm of SQP and heuristic algorithm of GA and traditional method (statistical method) by solving an example are compared and is shown that if the output of statistical method is used as start point of optimization using gradient based algorithm of SQP, the global answer will be derived.

کلیدواژه‌ها [English]

  • Launch vehicle design
  • Multidisciplinary design optimization
  • Genetic algorithm
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