نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران

2 استادیار - پژوهشکده سامانه های فضانوردی، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری ، تهران، ایران

10.22034/jsst.2021.1268

چکیده

هدف از این مقاله، ارائه مدل تخمین هزینه‌ی سامانه‌های پیشرانش فضایی سرمازا/نیمه‌سرمازا می‌باشد. در این راستا، انتخاب سامانه پیشرانش بهینه (از منظر نوع سوخت و اکسیدکننده) با هدف افزایش کارآیی و کاهش هزینه صورت پذیرفته است. سپس، نمونه‌های زوج سوخت و اکسیدکننده سامانه پیشرانش بر مبنای مشخصات جرمی – انرژتیک (وزن موتور – ضربه ویژه) سامانه‌ی پیشرانش و همچنین نوع سیکل کاری موتور با نگاه به امکان‌پذیری ماموریت، تعیین می‌شود. برای این منظور، روندنمایی برای اجرا و استفاده از مدل تخمین هزینه‌ی پیشنهادی تدوین شده است. در این روندنما، از روابط ریاضی موجود مدل تخمین هزینه استخراج می‌شود و با استفاده از مدل‌های موجود مورد صحه‌گذاری قرار می‌گیرد. در نهایت خروجی این روندنما، نمودار هزینه- کارآیی (ضربه ویژه) برای هفت زوج سوخت و اکسیدکننده، انتخاب موتور براساس بیشینه ضربه ویژه، ایجاد فضای جستجوی طراحی برای بهینه‌سازی هزینه-زمان در پروژه‌های فضایی می‌باشد.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Cost Estimation Model Presentation for Cryogenic/Semi-Crogenic Space Propulsion Systems

نویسندگان [English]

  • Mostafa Jafarpanah 1
  • Hassan Naseh 2

1 Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran

2 Assistant Professor, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran

چکیده [English]

The purpose of this paper is to present the cost estimation model for Cryogenic/Semi-Crogenic space propulsion systems. Therefore, the space propulsion system selection from fuel and oxidizer type aspect and achieving the maximum performance and minimum cost has been performed. Then, the fuel and oxidizer pair samples based on the mass – energy specifications (engine weight- specific impulse) and engine operation cycle type with respect to the mission possibility has been determined. To this end, the algorithm for implementing and using the proposed cost estimation model has been designed. In this algorithm, the proposed cost estimation model is developed based on the existing cost estimation relationship and verified by comparing the existing models. Finally, the outputs in the algorithm are cost-performance (specific impulse) graph for the seven fuels and oxidizer pairwise, engine selection based on achieving maximum specific impulse and providing the design space searches for the cost and time optimization in the space projects.

کلیدواژه‌ها [English]

  • Cost Estimation Model
  • Space propulsion system
  • Fuel and Oxidizer Pairwise
  • cryogenic
  • Semi-Crogenic
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