Journal of Space Science and Technology

Journal of Space Science and Technology

Reliability Based Design of a Space System in the Conceptual Design Phase

Document Type : Original Research Paper

Authors
1 Ph.D. Graduate, 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
Abstract
Achieving new technologies with high reliability while reducing the cost and time of the design cycle is one of the most significant challenges in developing complex systems. This paper discusses the reliability-based design of a space system during the conceptual design phase. Generally, there are eight steps in designing for reliability. As applied to a liquid propellant engine with electro-pump technology, these steps include planning, determination of failure modes, reliability modeling, reliability allocation, propagation of uncertainty, implementation of the chosen method in reliability analysis, reliability prediction, and reliability evaluation. Each step contains sub-steps that follow in a specific order.In the second step, the prediction of failure modes is carried out using two FMEA methods alongside design constraints. The third step involves developing the reliability block diagram for the electro-pump. In the fourth step, various reliability feature methods are introduced and reviewed. The fifth step presents four approaches to investigate uncertainty: sampling methods, analytical methods such as FORM and SORM, polynomial estimation using Taylor series, and advanced methods like random expansion.Subsequently, the uncertainty in the electro-pump engine is addressed alongside the limited functions in the electro-pump engine. Finally, in the seventh step, the reliability evaluation of the electro-pump engine is discussed. This evaluation is conducted to validate the proposed method, where reliability is determined using two indicators: specific impulse and mass ratio (initial mass to final mass).
Keywords
Subjects

Article Title Persian

طراحی بر مبنای قابلیت اطمینان یک سامانه فضایی در فاز طراحی مفهومی

Authors Persian

حمیدرضا علی محمدی 1
حسن ناصح 2
1 دکتری، پژوهشگاه هوافضا، وزارت علوم تحقیقات و فناوری، تهران، ایران
2 استادیار، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
Abstract Persian

دستیابی به فناوری‌های نوین با قابلیت اطمینان بالا، همراه با کاهش هزینه و زمان چرخه طراحی، یکی از مهم‌ترین چالش‌های صنایع پیچیده می‌باشد. در این مقاله به طراحی بر مبنای قابلیت اطمینان یک سامانه فضایی در فاز طراحی مفهومی پرداخته می‌‌شود. به‌طور معمول در طراحی بر مبنای قابلیت اطمینان، هشت گام اصلی وجود دارد، اولین گام، طرح‌ریزی و هفت گام بعدی طراحی بر مبنای قابلیت اطمینان موتور سوخت مایع الکتروپمپ را می­‌توان در قالب گام‌­های تعیین مدهای شکست؛ مدل­‌سازی قابلیت اطمینان؛ تخصیص قابلیت اطمینان؛ انتشار عدم قطعیت؛ پیاده‌سازی روش انتخابی در تحلیل قابلیت اطمینان؛ پیش‌­بینی قابلیت اطمینان و ارزیابی قابلیت اطمینان بیان نمود. در هر یک از گام­‌های فوق، زیرگام­‌هایی به‌ترتیب زیر صورت می­‌گیرد : در گام دوم، پیش‌بینی مدهای شکست براساس دو روش FMEA و قیود طراحی، انجام می‌­گیرد. در گام سوم، به زیر گام بلوک دیاگرام قابلیت اطمینان الکتروپمپ پرداخته می­‌شود. در گام چهارم، انواع روش­‌های تخصیص قابلیت اطمینان معرفی و بررسی می‌­شوند. در گام پنجم، چهار نگرش برای بررسی انتشار عدم قطعیت (روش­‌های نمونه­‌برداری، روش‌­های تحلیلی نظیر، روش (FORM) و (SORM)، تخمین چند اسمی با استفاده از تیلور، روش‌­های پیشرفته مانند گسترش تصادفی) معرفی و بررسی شده است. در گام ششم، به زیرگام انتشار عدم قطعیت در موتور الکتروپمپ و همچنین توابع حدی در موتور الکتروپمپ و در نهایت در گام هفتم به ارزیابی قابلیت اطمینان موتور الکتروپمپ پرداخته شده است. در این ارزیابی که به‌منظور صحه­‌گذاری بر روش پیشنهادی صورت پذیرفته است، قابلیت اطمینان با دو شاخص ایمپالس ویژه و نسبت جرمی (جرم اولیه به جرم نهایی)، مورد ارزیابی قرار می­‌گیرد.

Keywords Persian

طراحی برمبنای قابلیت اطمینان
موتور سوخت مایع
الکتروپمپ
قابلیت‌اطمینان
گام‌های پیاده‌سازی
طراحی مفهومی
[1] D. Linden, Handbook of Batteries, Advanced Batteries for Electric Vehicles and Emerging Applications. New York: McGraw–Hill, 2001.
[2] L. Sang-Bok, L. Tae-Kyu, and R. Tae-Seong, "Design optimization of liquid rocket engine using genetic algorithms," Journal of the Korean Society of Propulsion Engineers, vol. 16, no. 2, pp. 25-33, 2012.
[3] J. D. Shelton, R. A. Frederick, and A. W. Wilhite, "Launch vehicle propulsion design with multiple selection criteria," Journal of Spacecraft and Rockets, vol. 43, no. 4, pp. 893-902, 2006, https://doi.org/10.2514/1.16919.
[4] A. Jafarqoli, D. Ramsh, J. Abiyat, and M. J. Montazeri,"Liquid propulsion design, morphology and structure," Iranian Aerospace Industries Organisation Structure. 2005, (in Persian).
[5] P. Bafrani, "Structural design optimization of combustion chamber of liquid propellant engine using evolutionary algorithms," Faculty of Modern Sciences and Technologies, 2013, (in Persian).
[6] H. Karimi, "Design of liquid propellant engines," K.N. Toosi University of Technology, Tehran, 2012 (in Persian).
[7] D. Way and J. Olds, "SCORES-Web-based rocket propulsion analysis for space transportation system design," in 35th Joint Propulsion Conference and Exhibit, 1999, https://doi.org/10.2514/6.1999-2353.
[8] K.-S. Jeon, J.-W. Lee, C. Lee, and J. W. Chang, "Optimal gas generator design for the liquid rocket engine," in 42nd AIAA Aerospace Sciences Meeting and Exhibit, 2004, https://doi.org/10.2514/6.2004-32.
[9] A. A. Kazlov, Propellant, Schematic and Main Parameters Selection for Liquid Propellant Rocket Engines, MAI Press ,1997, (in Russian).
[10] A. A. Kazlov, Control and Feed System’s Elements of Liquid Propellant Rocket Engines, Russian, Mashinostroenie Press: Moscow, 1988, (in Russian).
[11] J. M. Brillouet et al., "The tannosome is an organelle forming condensed tannins in the chlorophyllous organs of tracheophyta," Annals of Botany, vol. 112, no. 6, pp. 1003-1014, 2013, https://doi.org/10.1093/aob/mct168.
[12] S. Lee, T. Lim, and T.-S. Roh, "Development of a system analysis program for a liquid rocket engine," Journal of Mechanical Science and Technology, vol. 29, pp. 2375-2380, 2015.
[13] G. Cai, J. Fang, Y. Zheng, X. Tong, J. Chen, and J. Wang, "Optimization of system parameters for liquid rocket engines with gas-generator cycles," Journal of Propulsion and Power, vol. 26, no. 1, pp. 113-119, 2010, https://doi.org/10.2514/1.40649.
[14] F. A. d. S. Mota, J. N. Hinckel, E. M. Rocco, and H. Schlingloff, "Modeling and analysis of a lox/ethanol liquid rocket engine," Journal of Aerospace Technology and Management, vol. 10,  2018, Art. no. 3018, https://doi.org/10.5028/jatm.v10.914.
[15] A. Okninski, J. Kindracki, and P. Wolanski, "Multidisciplinary optimisation of bipropellant rocket engines using H2O2 as oxidiser," Aerospace Science and Technology, vol. 82, pp. 284-293, 2018, https://doi.org/10.1016/j.ast.2018.08.036.
[16] H. Naseh, H. Ali Mohammadi, and F. Ommi, "A new approach in the design of complex products," in 5th International Conference on Reliability and Safety Engineering, Iran, 2018, (in Persian).
[17] N. Soldà and D. Lentini, "Opportunities for a liquid rocket feed system based on electric pumps," Journal of Propulsion and Power, vol. 24, no. 6, pp. 1340-1346, 2008, https://doi.org/10.2514/ 1.35074.
[18] P. P. Rachov, H. Tacca, and D. Lentini, "Electric feed systems for liquid-propellant rockets," Journal of Propulsion and Power, vol. 29, no. 5, pp. 1171-1180, 2013, https://doi.org/10.2514/1.B34714.
[19] H. D. Kwak, S. Kwon, and C.-H. Choi, "Performance assessment of electrically driven pump-fed lox/kerosene cycle rocket engine: comparison with gas generator cycle," Aerospace Science and Technology, vol. 77, pp. 67-82, 2018, https://doi.org/10.1016/j.ast.2018.02.033.
[20] D. Ramesh, "Development of static and dynamic optimization algorithm of closed cycle cryogenic propulsion systems," Ph.D. dissertation, K. N. Toosi University of Technology, Tehran, Iran, 2013, (in Persian).
[21] H. Alimohammadi, H. Naseh, and F. Ommi, "An Integrated methodology applied for reliability based multi-disciplinary design optimization in epfe with lox/kerosene," Reliability Engineering & System Safety, vol. 240, 2023, Art. no. 109570, https://doi.org/10.1016/j.ress.2023.109570.
[22] H. R. Alimohammadi, H. Naseh, and F. Ommi, "A new synthetic metamodel methodology for liquid‐propellant engine's cooling system optimization," Heat Transfer, vol. 50, no. 1, pp. 907-941, 2021, https://doi.org/10.1002/htj.21911.
[23] H. R. Alimohammadi, H. Naseh, and F. Ommi, "A novel framework for liquid propellant engine’s cooling system design by sensitivity analysis based on RSM and multi-objective optimization using PSO," Advances in Space Research, vol. 67, no. 5, pp. 1682-1700, 2021, https://doi.org/10.1016/j.asr.2020.11.018.
[24] H. R. Alimohammadi and R. Aghaei-Togh, "Multi-objective multidisciplinary design optimization of liquid-propellant engines thrust chamber based on a surrogate model," Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 237, no. 14, pp. 3215-3229, 2023, https://doi.org/10.1177/09544100231182268.
[25] S. M. Hashemi Dolabi, "Multi-subject design of space launch vehicle of liquid propellant based on reliability by fuzzy set theory method," Ph.D. dissertation, K. N. Toosi University of Technology, Tehran, Iran, 2013, (in Persian).
[26] T. Fossnes, K. Forsberg, R. Wray, G. Fisher, and W. Mackey, Systems Engineering Handbook, International Council on Systems Engineering (INCOSE), 2000.
[27] H. Naseh, H. R. Alimohammadi, and F. Ommi, "Increasing the reliability of the country's space launch vehicle by replacing a new generation of engines," in 5th International Conference on Reliability and Safety Engineering, Shiraz, Iran, 2018, (in Persian).
[28] H. Naseh, H. R. Alimohammadi, F. Ommi, and F. Ommi, "Design and multi-subject optimization of electro-pump liquid propellant engines with regard to reliability," Ph.D. dissertation, Aerospace Research Institute, Tehran, Iran 2021,(in Persian).

  • Receive Date 05 June 2023
  • Revise Date 12 September 2023
  • Accept Date 25 September 2023
  • First Publish Date 25 September 2023