نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 هیئت علمی دانشگاه اصفهان، اصفهان، ایران

2 مجتمع دانشگاهی مکانیک، دانشگاه صنعتی مالک‌اشتر، تهران، ایران

چکیده

در این مقاله به ارائۀ الگوریتم و نرم‌افزاری جامع جهت طراحی مفهومی موتورهای موشکی با مولفه-های پیشران سرمازا، پرداخته شده است. در الگوریتم، پنج چرخه کاربردی تغذیۀ تحت فشار، مولدگازی، احتراق مرحله‌ای، انبساطی بسته و باز مدلسازی شده است. به منظور صحت‌سنجی، موتورهایVulcain و HM7B، بازطراحی و مقایسۀ نتایج حاصل با اطلاعات واقعی بیانگر خطای کمتر از 5 درصد پارامترهای اصلی طراحی و کمتر از 20 درصد درسایر پارامترها است که در مرحلة طراحی مفهومی از دقت کافی برخوردارند. از مزایای این نرم‌افزار وجود قریب150 پارامتر و 14 نمودار مربوط به رفتار جریان در محفظة تراست و جلیقة خنک‌کاری در خروجی است که امکان مطالعة پارامتریک تاثیر تغییرات ورودی‌ها بر خروجی‌ها را فراهم می‌نماید. مدلسازی توابع موجود در الگوریتم و محاسبات مربوط به احتراق با استفاده از نرم‌افزارهایMATLABوCEAانجام گرفته و نهایتاً با ادغام در محیط برنامه‌نویسی Visual studio و با استفاده از زبان برنامه‌نویسی C#، نرم‌افزاری با رابط کاربری گرافیکی کاربرپسند ارائه شده است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Developing a universal Software for the Conceptual Design of Cryogenic Rocket Propulsion System

نویسندگان [English]

  • Nourbakhsh Fouladi 1
  • Neda sadat Seddighi renani 2

1 Isfahan university, Isfahan, Iran

2 Faculty of Mechanical Engineering, Maleke-Ashtar University of Technology, Tehran, Iran

چکیده [English]

In this article, a universal algorithm and engineering software is presented for the conceptual design of cryogenic rocket propulsion system. The algorithm consisting five engine working cycles: pressure fed, gas generator, staged combustion, closed and opened expansion cycles. For validation, the Vulcain and HM7Bengines were redesigned, the obtained results certifies that the main design parameters have less than 5% errors and the other less than 20%. One of the advantages of this software is the presence of abut150 parameters in the output and 14 diagrams related to the flow behavior in the thrust chamber and cooling vest, which allows the parametric study of the effect of input changes on the outputs.The modeling of mathematical functions and the combustion has been done, by using the MATLAB and CEAsoftware. Finally, by merging in Visual studio programming environment and with the help of C# programming language, a software with GUI is presented.

کلیدواژه‌ها [English]

  • Rocket Propulsion Design Algorithm
  • Liquid Propellant Rocket Propulsion System
  • Rocket Propulsion Conceptual Design
  • Cryogenic Rocket Engine
  • Rocket Propulsion Design Software
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