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

Jafarpanah, Mostafa; Naseh, Hassan

doi:10.22034/jsst.2021.1268

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

Document Type : Original Research Paper

Authors

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

10.22034/jsst.2021.1268

Abstract

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.

Keywords

Cost Estimation Model

Space Propulsion System

Fuel and Oxidizer Pairwise

Cryogenic

Semi-Crogenic

20.1001.1.20084560.1400.14.4.3.6

Subjects

System Design, Space Propulsion and Space System Simulation

Article Title Persian

ارائه مدل تخمین هزینه‌ سامانه‌های پیشرانش فضایی سرمازا/نیمه‌سرمازا

Authors Persian

مصطفی جعفرپناه ¹

حسن ناصح ²

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

Abstract Persian

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.

Keywords Persian

مدل تخمین هزینه

زوج سوخت و اکسیدکننده

سامانه‌ی پیشرانش فضایی

سرمازا

نیمه‌سرمازا

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