Assessment of the efficiency of hot helium tank pressurization systems for oxygen-propelled rocket engines
Heading:
| 1Sukhyi, KM, 2Voit, SM, 1Mitikov, Yu.O, 2Spirkin, SV, 1Sukha, IV 1Ukrainian State University of Science and Technologies, Dnipro, Ukraine 2State Enterprise “Production Association Yuzhny Machine-Building Plant named after O. M. Makarov”, Dnipro, Ukraine |
| Space Sci. & Technol. 2025, 31 ;(4):03-11 |
| https://doi.org/10.15407/knit2025.04.003 |
| Publication Language: English |
Abstract: For the first time, a study of the design has been conducted, and a detailed weight summary of the hot helium pressurization system for an oxidizer tank of the first stage of a launch vehicle (LV) has been presented; the propulsion system of this LV uses boiling oxygen ̶̶̶ RG-1 as propellants. The oxidizing generator gas was considered as the heat exchanger heat carrier. The weight of this system was also evaluated for an alternative common heat carrier — reduced generator gas. A good correlation was shown between the obtained results and known data from other pressurization systems.
The efficiency of hot helium pressurization systems is demonstrated in the case of multiple reuses of the first stage of an LV. It is also reasonable to use it for the dual activation of the liquid rocket engine (LRE) of the second stage of an LV. In these cases, arising issues are solved using well-established, proven solutions. However, an analysis of technical literature shows that alternative solutions have not been thoroughly studied. In other cases, considering the high cost, structural complexity, actual low reliability, and lack of weight advantages, the use of hot helium pressurization systems (PS) is hardly justified. This primarily concerns LREs with afterburning of generator gas, where oxidizing gas is used as the coolant in the heat exchanger.
It is also noted that it is necessary to provide helium reserves on board
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| Keywords: boiling oxygen, coolant, efficiency, hot helium, pressurization systems, propulsion systems, system weight |
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https://rocketspace.dp.ua/rst/article/download
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https://bugulma-lada.ru/different/toplivnaya-para-sp
2. Barmin, I.V. (2005). Technological objects of the ground infrastructure of rocket and space technology (Book 1). Moscow: Poligrafiks RPK. 420 pages.
3. Beliaev, N.M. (1976). Systems of pressurization of rocket fuel tanks. Moscow: Mashinostroenie. 335 pages.
4. Biruk, V.V., Smorodin, A.V., Shepelev, A.I., et al. (2013). Pressurization system of the rocket carrier fuel tanks using generator gas heat. Vestnik of SGAU, 3(4), 35-38.
https://doi.org/10.18287/1998-6629-2013-0-3-1(41)-35-39
5. Degtyarev, A.V., Kushnarev, A.P., Popov, D.A., et al. (2014). Rocket for space use of ultra-small class. Space Technology. Rocket Weapons: Scientific and technical works of GKB "Yuzhnoe", 1, 14-20.
6. Hermsen, R.J. (2017). Cryogenic propellant tank pressurization: Practical investigation on the collapse factor for small, high-pressure, cryogenic rocket propellant tanks. 161 pages.
7. Kazakevich, M., Husarova, I., Kazakevich, V., Manko, T., Khoroshylov, V., Kozis, K., Osinovyy, G., Sukha, I., & Zaichuk, O. (2024). Carbon plastics for reusable hypersonic flight vehicles. Voprosy Khimii i Khimicheskoi Tekhnologii, 6, 150-157.
https://doi.org/10.32434/0321-4095-2024-157-6-150-157
8. Kravchenko, I., Mitikov, Yu., Torba, Yu., & Zhyrkov, O. (2021). Use of low-potential heat for heating helium in rocket-carrier tank pressurization systems. Scientific Horizons, 24(7), 9-19.2021.9-19
https://doi.org/10.48077/scihor.24(7).2021.9-19
9. Klyueva, O.G. (2007). Creation of a unified heat exchanger for a single-chamber liquid rocket engine. Proceedings of NPO Energomash, 25, 286-301.
10. Manko, T., Husarova, I., Kozis, K., Sukha, I., Zaichuk, O., & Sukhyy, K. (2025). Production of fiberglass plastics using infrared heating. Voprosy Khimii I Khimicheskoi Tekhnologii, 1, 94-102.
https://doi.org/10.32434/0321-4095-2025-158-1-94-102
11. Mitikov, Yu., Andrievskyi, M. (2021). Approach to solution of tank with hydrogen peroxide pressurization by its decomposition products. Space Science & Technology, 27(5), 3-10.
https://doi.org/10.15407/knit2021.05.003
12. Mitikov, Yu.A., Antonov, V.A., Voloshin, M.L., Logvinenko, A.I. (2012). Ways to improve the reliability and safety of rocket complexes. Aerospace Technic and Technology, 3(90), 30-36.
13. Mitykov, Y. O., Bucharskyi, V. L., & Ponomariov, O. M. (2023). Heat exchangers of rocket engines and power plants based on renewable energy sources: Designs and calculation methods [Textbook]. Dnipro: Sova LLC. 280 p.
14. Mitykov, Y. O., & Sedchenko, M. S. (2023, June 1). Critical analysis of helium gas cylinder pressurization systems for rocket engine fuel tanks. Energy and Thermotechnics, CIMS 2023.
https://fti.dp.ua/conf/2023/06012-0637/
15. Mitikov, Yu., Shynkarenko, O. (2022). Reduction of the pressurization system final mass for a modern rocket. Journal of Aerospace Technology and Management, 14, e0122, 1-10.
https://doi.org/10.1590/jatm.v14.1238
16. Mitikov, Yu., & Tatarinov, K.A. (2017). Analysis of ways to improve the fuel tank pressurization systems of rocket engines. Visnyk DNU im. O. Honchara. Series: Rocket and Space Technology, 25(20), 50-56.
17. Mitikov, Yu. (2012). Use of vortex rings for pressurization of rocket engine fuel tanks. East European Journal of Advanced Technologies, 5/7(59), 30-33.
18. Mikhailchishin, R.V. (2017). Features of the pneumo-hydraulic fuel supply system using cryogenic components of oxygen-methane. Space Technology. Rocket Weapons, 2, 35-40.
19. Mosieiko, V.A., & Mitikov, Yu. (2015). Physical modeling of in-tank processes in rocket propulsion systems. Bulletin of Engine Engineering, 1, 45-49.
20. Naoumov, V.I., Krioukov, V.G., Abdullin, A.L., & Demin, A.V. (2019). Pressurization of liquid propellant rocket engine tanks. In Chemical Kinetics in Combustion and Reactive Flows: Modeling Tools and Applications (pp. 334-379). Cambridge University Press.
https://doi.org/10.1017/9781108581714.009
21. Petrenko, R.M. (2023). Advantages of high-temperature generator pressurization of tanks with liquefied natural gas. Visnyk DNU im. O. Honchara. Series: Rocket and Space Technology, 4(28), 53-61.
https://rocketspace.dp.ua/rst/article/download
22. Romanov, M. (2019). About the Rutherford engine. Alpha Centauri. https://thealphacentauri.net/25345-o-dvigatele-rutherford/
23. Sukhyi, K.M, Voyt, S.M., Mitikov, Yu.O., & Sukha, I.V. (2025). Method for polytropic pressurization of a rocket carrier tank. Patent Application a202500547. Ukraine. B64D 37/24, B64G 1/24, B64G 1/40, F02K 9/42.
24. Toplivnaya para spirt - perekis' vodoroda. (n.d.). Besedy o raketnykh dvigatelyakh. Retrieved from
https://bugulma-lada.ru/different/toplivnaya-para-sp