نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران

چکیده

تقریباً در تمامی ماهواره‌برها از سیستم پیشرانش توربوپمپی استفاده شده است. با ارتقاء فناوری‌های ساخت، خصوصًا در استفاده از سازه‌های کامپوزیتی و سبک، استفاده از سیستم‌های پیشرانش غیر توربوپمپی با توجه به کاهش هزینه‌های عملیاتی مورد توجه قرار گرفته است. در این تحقیق به طراحی بهینه چندموضوعی یک ماهواره‌بر دو طبقه با استفاده از سیستم پیشرانش تحت فشار برای هر دو طبقه پرداخته شده است. دو دسته اصلی سیستم‌های پیشرانش غیر توربوپمپی شامل سیستم تغذیه رگلاتوری و دمشی در ساختارهای مختلف در دو طبقه ماهواره‌بر مورد ارزیابی قرار گرفته است. استخراج جواب بهینه و ممکن مأموریت پرتابگر نیز به عنوان یک متغیر طراحی در الگوریتم بهینه‌سازی اضافه شده است. بر این اساس پرتابگری برای رسیدن ارتفاع مداری مشخص با قدرت حمل حداکثر بارمحموله و حداقل جرم برخاست برای هر ساختار پرتابگر استخراج و معرفی گردیده است. برای این منظور از چارچوب طراحی بهینه چندموضوعی AAO استفاده گردیده است. بهینه‌ساز سطح سیستم و زیرسیستم الگوریتم تلفیقی GA-SQP انتخاب شده است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Multi-disciplinary optimization conceptual design of the launcher based on non-turbopump propulsion systems

نویسندگان [English]

  • Hanieh Eshaghnia
  • Mehran Nosratollahi
  • Amirhossain Adami
  • Hadi Dastoury

Aerospace University Complex, Malik Ashtar University of Technology, Tehran, Iran

چکیده [English]

Turbopump propulsion systems have been used in almost all launch vehicles. With the advancement of manufacturing technologies, especially in the use of composite and lightweight structures, the use of non-turbopump propulsion systems has been considered due to the reduction of operating costs. This study has been investigated the multi-disciplinary optimization design of a two-stage launch vehicle using a pressure-fed propulsion system for both stages. Two main propulsion systems including gas-pressure and self-pressure feeding systems, have been evaluated in different configurations on two launcher stages. To extracting the optimum and possible solution, the launcher mission also has been added as a design variable in the optimization algorithm. The launcher has been extracted and introduced for each specific configuration of the launcher to achieve a certain orbital altitude with the maximum carrying payload and minimum gross mass. For this purpose, the AAO multidisciplinary optimization design framework has been used. The system-level and subsystem optimizer of the GA-SQP algorithm have been chosen.

کلیدواژه‌ها [English]

  • Launcher
  • Multidisciplinary optimization design
  • Pressure-fed propulsion system
  • Gas-pressure and self-pressure system
  • system design
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