Journal of Space Science and Technology

Journal of Space Science and Technology

Investigating of the Leap Required in Effective Technologies for SSTO Design Using MDO

Document Type : Original Research Paper

Authors
Aerospace University Complex, Malek Ashtar University of Technology, Tehran, Iran
Abstract
The possibility of injecting a satellite into orbit using a single-stage carrier has been one of the challenges far from human hands since the past. Even in the past, to prove the impossibility of achieving this wish, various mathematical relations and equations have been expressed. But what has filled the hopes in recent years is the improvement of the technology level. The answer to the question of whether it is possible to achieve the circuit using a single-stage carrier with the current level of technology has recently received attention. In this research, an overview of the existing technologies and single-stage launchers is discussed and the path from the existing technology to the required technology is extracted. For this purpose, after modeling different subsystems, the design framework based on multi-subject optimal conceptual design and GA-SQP optimization algorithm has been developed and validated. Then, multi-objective optimal design (MDO) of a single-stage satellite carrier has been carried out and the feasibility of achieving a single-stage satellite carrier has been evaluated. Despite extracting the best structure, the results indicate the impossibility of achieving this product with the current level of technology. In the following, the minimum amount of technology jump required by each technology, including issues such as release, propulsion and structure, to achieve this task was carried out based on multi-objective optimal analysis (MDA) and the results for each technology are presented separately.
Keywords
Subjects

Article Title Persian

بررسی جهش مورد نیاز در فناوری‌های موثر در طراحی SSTO با استفاده از روش بهینه‌سازی چندموضوعی

Authors Persian

فاطمه قربانی تزری
مهران نصرت الهی
امیرحسین آدمی
علیرضا آهنگرانی فراهانی
کارشناس ارشد، مجتمع دانشگاهی هوافضا، دانشگاه مالک اشتر، تهران، ایران کارشناس آزمایشگاه پهپاد دانشگاه خواجه نصیرالدین طوسی، تهران، ایران
Abstract Persian

امکان تزریق ماهواره به مدار با استفاده از یک حامل تک مرحله‌ایی به‌عنوان یکی از چالش‌های دور از دست بشر از گذشته تاکنون بوده است. حتی در گذشته، برای اثبات عدم امکان دستیابی به این آرزو، روابط ریاضی و معادلات مختلفی بیان گردیده است. اما آنچه امیدها را در سا‌‌‌ل‌های اخیر پر رنگ نموده است ارتقاء سطح فناوری است. پاسخ به این سوال که آیا با سطح فناوری کنونی امکان دستیابی به مدار با استفاده از یک حامل تک مرحله‌ایی تا چه اندازه قابل دستیابی است اخیراً مورد توجه قرار گرفته است. در این پژوهش به بررسی اجمالی سیر تکاملی و تکنولوژی‌های موجود پرتابگرهای تک مرحله‌ای تا مدار پرداخته شده و مسیر رسیدن از فناوری موجود به فناوری مورد نیاز استخراج می‌گردد. برای این منظور، پس از مدل‌سازی زیرسیستم‌های مختلف، چارچوب طراحی برپایه طراحی مفهومی بهینه چندموضوعی و با الگوریتم بهینه‌سازی GA-SQP تدوین گردیده و صحه‌گذاری شده‌است. سپس، طراحی بهینه چندموضوعی  (MDO) ماهواره‌بر تک مرحله‌ای انجام پذیرفته و امکان‌سنجی دستیابی به یک ماهواره‌بر تک مرحله‌ایی مورد ارزیابی قرار گرفته است. علی‌رغم استخراج بهترین ساختار، نتایج حاکی از عدم امکان دستیابی به این محصول با سطح تکنولوژی موجود است. در ادامه حداقل میزان جهش تکنولوژی مورد نیاز هر یک از فناوری‌ها، شامل موضوعاتی نظیر رهایش، پیشرانش و سازه، برای دستیابی به این مهم براساس تحلیل بهینه چندموضوعی (MDA) انجام پذیرفته و نتایج برای هر فناوری به‌طور جداگانه ارائه شده است.

Keywords Persian

طراحی مفهومی
چارچوب طراحی
طراحی چند موضوعی
تک‌طبقه تا مدار
بهینه‌سازی
[1] F. Ghorbani, "Conceptual design and analysis of a single-stage satellite up to SSOT orbit," M.S. thesis, Malek Ashtar University of Technology, Tehran, Iran, 2018. (in Persian).
[2] wikipedia, "Single-stage-to-orbit." wikipedia.org. [Online]. Available: https://en.wikipedia.org/wiki/Single-stage-to-orbit.
[3] A. H. Adami , F. Ghorbani, "Investigating methods of sending medium-weight satellites by single-stage launchers," in 17th International Conference of Iranian Aerospace Society, Tehran, Iran, 2018, (in Persian).
[4] H. Yoshida, M. M. Micci, M. Nakane, K. Yamaguchi, and Y. Ishikawa, "Integrated optimization for single-stage-to-orbit using a pulse detonation engine," Journal of Spacecraft and Rockets, vol. 56, no. 4, pp. 983-989, 2019, https://doi.org/10.2514/1.A34341.
[5] O. Prakash and R. Singh, "Flight dynamics analysis using high altitude & mach number for generic air-breathing hypersonic vehicle," in AIAA Propulsion and Energy Forum, (virtual event), 2021, https://doi.org/10.2514/6.2021-3271.
[6] J. B. Vos, D. Charbonnier, A. Marwege, A. Guelhan, M. Laureti, and S. Karl, "Aerodynamic investigations of a vertical landing launcher configuration by means of computational fluid dynamics and wind tunnel tests," in AIAA SciTech Forum, San Diego, CA, 2022, https://doi.org/10.2514/6.2022-1308.
[7] E. Sorto-Ramos, K. Seyed Alavi, and B. Chudoba, "A parametric comparison of SSTO and TSTO space access vehicle concepts," in AIAA Scitech Forum, Orlando, 2022, https://doi.org/10.2514/6.2020-0549.
[8] X. Zhang, J. Feng, R. Mu, and J. Chen, "Feasibility study on SSTO rocket with an initial velocity given by EML," Journal of Spacecraft and Rockets, vol. 56, no. 1, pp. 241-247, 2019, https://doi.org/10.2514/1.A33946.
[9] R. Pradeep et al., "Conceptual design and contour optimization of altitude compensation nozzles for SSTO vehicles," in AIAA Propulsion and Energy Forum, (virtual event), 2020, https://doi.org/10.2514/6.2020-3922.
[10] S. Sundaria, A. K. Bhagat, and V. S. Kumar, "In silico studies on truncated aerospike nozzle with optimum cowl length for single stage to orbit vehicles," in 25th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Bengaluru, Karnataka, India, 2023, https://doi.org/10.2514/6.2023-3105.
[11] J. Robinson, G. Culver, R. Bishop, and E. Bright, "Life cycle analysis of a single stage to orbit (SSTO) reusable launch vehicle," in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, 2003, Art. no. 5264, https://doi.org/10.2514/6.2003-5264.
[12] R. Varvill and A. Bond, "A comparison of propulsion concepts for SSTO reusable launchers," Journal-British Interplanetary Society (JBIS), vol. 56, no. 3/4, pp. 108-117, 2003.
[13] S. Salvi, C. Paravan, and L. Galfetti, "SSTO reusable launchers: a critical comparison of propulsion concepts," in 9th European Conference for Aeronautics and Space Sciences (EUCASS), Lille Grand Palais, France, 2022, p. 31, https://doi.org/10.13009/EUCASS2022-4914.
[14] L. F. Pozas and L. V. R. de Arruda, "A new approach to integrate SSTO, MPC and RTO using online identified models," Journal of Control, Automation and Electrical Systems, vol. 29, no. 5, pp. 566-575, https://doi.org/10.1007/s40313-018-0397-4.
[15] R. He, P. Zhang, L. Liu, J. Wang, and D. Meng, "Study on trajectory optimization for single-stage-to-orbit space planes using gauss pseudospectral method," in 29th Chinese Control And Decision Conference (CCDC), Chongqing, China, 2017, pp. 5374-5379, https://doi.org/10.1109/CCDC.2017.7979452.
[16] H. Eshaghnia, M. Nosratollahi, and A. Adami, "Performance evaluation of a launch vehicle with non-turbopump propulsion system based on multidisciplinary analysis (MDA)," Journal of Space Science and Technology, vol. 14, no. 4, pp. 35-49, 2021, (in Persian) https://doi.org/10.22034/jsst.2021.1278.
[17] D. O. Stanley and W. M. Piland, "Technology requirements for affordable single-stage rocket launch vehicles," NASA Langley Research Center, Hampton, Virginia, Technical Reports 20040121139, 2004.
[18] D. C. Freeman, D. O. Stanley, C. J. Camarda, R. A. Lepsch, and S. A. Cook, "Single-stage-to-orbit - A step closer," Acta Astronautica, vol. 37, pp. 87-94, 1995, https://doi.org/10.1016/0094-5765(95)00087-G.
[19] "Access to space study," Office of Space Systems Development NASA Headquarters, Summary Report. TM-109693,1994.
[20] J. Hunt, "Airbreathing/rocket single-stage-to-orbit design matrix," in International Aerospace Planes and Hypersonics Technologies Conference, Chattanooga, TN, U.S.A., 1995, https://doi.org/10.2514/6.1995-6011.
[21] C. Eldred, "Evolution of NASA rocket SSTO concept," in Space Programs and Technologies Conference and Exhibit, Huntsville, AL, U.S.A., 1994, https://doi.org/10.2514/6.1994-4673.
[22] R. Norouzi, Design of an Airborne "Satellite Carrier with First-Class Reusability", M.D. Nosrat Elahi and A. H. Adami, Eds. Tehran, Iran: Malek Ashtar University of Technology, 2014.
[23] P. Kolodziej and D. Rasky, "A V-2/atlas approach to building SSTO launch vehicles," in 41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2003, Art. no. 2003-658, https://doi.org/10.2514/6.2003-658.
[24] D. E. Koelle, "Economics of small fully reusable launch systems (SSTO vs. TSTO)," Acta Astronautica, vol. 40, no. 2-8, pp. 535-544, 1997, https://doi.org/10.1016/S0094-5765(97)00142-2.
[25] D. E. Koelle, "Cost analysis for single-stage (SSTO) reusable ballistic launch vehicles," Acta Astronautica, vol. 30, pp. 415-421, 1993, https://doi.org/10.1016/0094-5765(93)90132-G.
[26] V. Balochestani, S. Davoodabdi Farahani, A. H. Adami, "Feasibility of propulsion system for single-stage orbital missions, "in First Regional Conference of Mechanical Engineering, Isfahan, Iran, 2010.(in Persian).
[27] A. W. Wilhite et al., "Advanced technologies for rocket single-stage-to-orbit vehicles," Journal of Spacecraft and Rockets, vol. 28, no. 6, pp. 646-651, 1991, https://doi.org/10.2514/3.26294.
[28] V. Balepin, M. Maita, and S. Murthy, "'Third way' of development of SSTO propulsion," in Space Plane and Hypersonic Systems and Technology Conference, Norfolk, VA, U.S.A., 1996, Art. no. AIAA-96-4495-CP, https://doi.org/10.2514/6.1996-4495.
[29] P. Hendrick and J. Vanderkerckhove, "Precompression influence on S.S.T.O. performance," in 5th International Aerospace Planes and Hypersonics Technologies Conference, Munich, Germany, 1993, https://doi.org/10.2514/6.1993-5030.
[30] D. Schmidt and J. Velapoldi, "Optimum mission performance and guidance for hypersonic single stage to orbit," in Guidance, Navigation, and Control Conference, San Diego, CA, U.S.A., 1996, https://doi.org/10.2514/6.1996-3904.
[31] J. L. Duparcq, E. Hermant, and D. Scherrer, "Turbojet-type engines for the airbreathing propulsion of reusable winged launchers, " in 41st Congress of the International Astronautical Federation, Dresden, Germany, 1990. https://doi.org/10.1016/0094-5765(93)90068-8.
[32] F. Creta and M. Valorani, "Optimal shape design of supersonic, mixed-compression, fixed-geometry air intakes for SSTO mission profiles," in 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Indianapolis, Indiana, 2002, https://doi.org/10.2514/6.2002-4133.
[33] J. Jia, W. Chen, and Z. Wang, "Aerodynamic parameter estimation for launch vehicles," in Autonomous Trajectory Planning and Guidance Control for Launch Vehicles, Z. Song, D. Zhao, and S. Theil, Eds. Singapore: Springer Nature Singapore, 2023, pp. 201-213, https://doi.org/10.1007/978-981-99-0613-0_7.
Volume 18, Issue 1
2025
Pages 1-23

  • Receive Date 03 July 2024
  • Accept Date 07 July 2024
  • First Publish Date 08 July 2024