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
- Chakroborty and T. Bauer, "Using pressure-fed propulsion technology to lower space transportation costs," in 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Lauderdale- Florida, AIAA, 2004, p. 3358.
- Hosseini, A. Toloie, M. Nosratollahi and A. Adami, "Multidisciplinary design optimization of an expendable launch vehicle," in Proceedings of 5th International Conference on Recent Advances in Space Technologies-RAST2011, IEEE, 2011, pp. 702-707.
- Stanley, "Preliminary Design of a Pressurization System for Small Bipropellant Rocket Engines," University of Texas at Arlington (PhD Thesis), 2011.
- Hashemi, H. Darabi و J. Roshanian, “Comparison Between Traditional Method (Statistical Method) and Multidisciplinary Optimization Method (AAO) in Designing of a Lightweight Liquid Propellant LV,” Journal of Space Science and Technology, جلد 5, شماره 1, pp. 61-72, 2012.
- Nosratollahi, A. Novin zadeh, M. Zakeri and Y. Emadi nori, "Conceptual design of blowdown engine of upperstage," in 13th Conference of the Iranian Aerospace Association, Tehran, University of Tehran, Faculty of Science and New Technologies, 2013.
- r. Alikhani, M. Eskandari و H. Karimi, “Develop a conceptual design algorithm of a liquid rocket engine in pressurizing fed cycle based on performance parameters,” در 13th Conference of the Iranian Aerospace Association, Tehran, University of Tehran, Faculty of Science and New Technologies, 2013.
- Li, N. Yu, P. Zeng and G. Cai, "Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor," Science China Technological Sciences, vol. 56, no. 4, pp. 989-1000, 2013.
- Roshanian, H. Darabi و H. Zare, “Multidisciplinary Conceptual Design Optimization of Manned Launch Vehicle Using Combined Algorithm,” Aerospace Mechanics Journal, جلد 10, شماره 4, pp. 33-44, 2014.
- Sarzi-Amade, T. Bauer, J. Wertz and M. Rufer, "Sprite, a very low-cost launch vehicle for small satellites," in Proceedings of the 12th Reinventing Space Conference, Springer, 2017, pp. 165-178.
- Adami, M. Mortazavi and M. Nosratollahi, "Multidisciplinary design optimization of hydrogen peroxide monopropellant propulsion system using GA and SQP," International Journal of Computer Applications, vol. 113, no. 9, 2015.
- A. Hurlbert, M. J. Atwell, J. C. Melcher and R. L. Morehead, "Integrated Pressure-Fed Liquid Oxygen/Methane Propulsion Systems-Morpheus Experience, MARE, and Future Applications," in 52nd AIAA/SAE/ASEE Joint Propulsion Conference, AIAA, 2016, p. 4681.
- Matsumoto, S. Okaya, H. Igoh and J. Kawaguchi, "Concept of a self-pressurized feed system for liquid rocket engines and its fundamental experiment results," Acta Astronautica, vol. 133, pp. 166-176, 2017.
- Carroll, "System sizing design of liquid oxygen/ liquid methane DAEDALUS sub-orbital vehicle," Master of science in mechanical engineering, the university of Texas, El Paso, 2017.
- Brevault, M. Balesdent and S. Defoort, "Preliminary study on launch vehicle design: Applications of multidisciplinary design optimization methodologies," Concurrent Engineering, vol. 26, no. 1, pp. 93-103, 2018.
- C. Melcher and R. L. Morehead, "Combustion stability characteristics of the project morpheus liquid oxygen/liquid methane main engine," in 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2014, p. 3681.
- Es'haghnia," Multidisciplinary design optimization of a two stage launcher with non-torbopump propulsion system,” MSc Thesis, Aerospace Engineering University Complex, Tehran, Malek Ashtar University of Technology, 2020.
- Brevault, M. Balesdent and A. Hebbal, "Multi-objective multidisciplinary design optimization approach for partially reusable launch vehicle design," Journal of Spacecraft and Rockets, vol. 57, no. 2, pp. 373-390, 2020.
- P. Sutton and O. Biblarz, Rocket propulsion elements, Canada: Wiley, 2017.
- D. Brown, Spacecraft Propulsion, Ohio: AIAA, 1930.
- K. Huzel and D. H. Huang, Modern Engineering for Design of Liquid-Propellant Rocket Engines, Washington: American Institute of Aeronautics and Astronautics, 1992.
- Adami, M. Mortazavi, M. Nosratollahi, M. Taheri and J. Sajadi, "Multidisciplinary design optimization and analysis of hydrazine monopropellant propulsion system," International Journal of Aerospace Engineering, vol. 2015, 2015.
- A. Silva Mota, "Modeling and Simulation of Launch Vehicles Using Object-Oriented Programming," Instito Nacional De Pesquisas Espaciais, São José, PhD Thesis, 2015.
- W. Humble, G. N. Henry and W. J. Larson, Space Propulsion Analysis and Design, New York, San Frencisco, Auckland Bogota: United states Department of Defence and the National Aeronautics and Space Adminstration- McGraw-Hill, Inc, 1997.
- Delalat, “Multidisciplinary design optimization of the passenger transmission system to the suborbital space,” MSc Thesis, Aerospace Engineering University Complex, Tehran, Malek Ashtar University of Technology, 2012.
- J. Masterman, "The Leon 1: A 3D Printed Liquid Methane/ Liquid Oxygen Pressure-fed Rocket Propulsion System," The Faculty of the Department of Aerospace Engineering San Jose State University, 2015.
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