دانش و فناوری هوافضا

دانش و فناوری هوافضا

طراحی بهینه سیستمی موشک بالستیک سوخت مایع با استفاده از روش مبتنی بر آموزش و یادگیری تحت عدم قطعیت

نوع مقاله : مقاله پژوهشی

نویسندگان
1 دانشجوی دکتری هوافضا، دانشگاه شهید بهشتی
2 دانشیار، دانشگاه شهید بهشتی
چکیده
این مقاله به طراحی بهینه و مقاوم یک موشک سوخت مایع تحت شرایط عدم قطعیت می‌پردازد. هدف آن، کاهش جرم موشک با حفظ پایداری طراحی در برابر تغییرات محیطی و عملیاتی است. طراحی بر اساس رویکرد کلاسیک سرعت مورد نیاز انجام شده و پیکربندی موشک و ترکیب سوخت با توجه به جرم محموله و برد پروازی تعیین می‌شود. پس از محاسبات جرم و هندسی، پارامترهایی مانند جرم اولیه، میزان سوخت و نیروی تراست موتور هر مرحله محاسبه می‌شود. صحت این روش با داده‌های موشک‌های مشابه دنیا ارزیابی شده و سپس با الگوریتم تکاملی مبتنی بر آموزش و یادگیری(TLBO)، پارامترهایی چون تراست نسبی اولیه، فشار محفظه احتراق و فشار خروجی نازل بهینه می‌شوند. در نهایت، با در نظر گرفتن عدم قطعیت در ضربه ویژه(Isp) مراحل اول و دوم و اعمال روش نمونه‌برداری مکعب لاتین (LHS) طراحی به گونه‌ای انجام می‌شود که علاوه بر حفظ مقاومت در برابر تغییرات، جرم موشک حداقل گردد.
کلیدواژه‌ها

موضوعات


عنوان مقاله English

Optimal system design of a liquid fuel missile using Teaching-Learning-Based-Optimization(TLBO) under uncertainty

نویسندگان English

maziar hoseini shalmaee 1
alireza toloei 2
1 Ph.D. Candidate of Aerospace Engineering, Shahid Beheshti University, Tehran, Iran
2 Associate Profess, Shahid Beheshti University
چکیده English

This paper focuses on the optimal and robust design of a liquid-fueled rocket under uncertainty conditions. The objective is to minimize the rocket's mass while maintaining design stability against environmental and operational variations. The design is based on the classical velocity requirement approach, where the rocket configuration and fuel composition are determined according to the payload mass and flight range. After performing mass and geometric calculations, parameters such as initial mass, fuel quantity, and thrust force for each stage are computed. The accuracy of the method is validated using data from similar rockets worldwide, and subsequently, parameters such as initial relative thrust, combustion chamber pressure, and nozzle exit pressure are optimized using the TLBO algorithm. Finally, considering uncertainty in the specific impulse (Isp) of the first and second stages and applying the Latin Hypercube Sampling (LHS) method, the design is refined to ensure robustness against variations while minimizing the rocket’s mass.

کلیدواژه‌ها English

missile
systematic design
evolutionary optimization
uncertainty
robust optimum
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