Approach to solution of tank with hydrogen peroxide pressurization by its decomposition products
Рубрика:
1Andriievskyi, MV, 2Mitikov, Yu.O 1Propulsion Systems Department of the Ukrainian branch of Skyrora Ltd, Edinburgh, UK; Oles Honchar National University of Dnipro, Dnipro, Ukraine 2Oles Honchar National University of Dnipro, Dnipro, Ukraine |
Space Sci. & Technol. 2021, 27 ;(5):003-010 |
https://doi.org/10.15407/knit2021.05.003 |
Язык публикации: English |
Аннотация: Aim. To find and confirm the possibility of hydrogen peroxide tank pressurization using high-temperature pressurization gas (~1100К) with a high percentage of steam (up to 70%) without its losses.
Research methods. Mathematical modeling of pressurization system parameters with the theory of mass transfer and thermodynamic of variable mass bodies have been used.
Results. The conducted research allowed us to find and confirm the possibility of using a new pressurization method with additional sources of heat and elaborate recommendations for its appliance during pressurization time.
Scientific novelty. The main processes have been determined, which prevent implementation of the efficient high-temperature pressurization system of the tank with the hydrogen peroxide using peroxide decomposition products. The main obstacle is the volume condensation of vapor in the free volume of the tank when heat exchange processes with boundary surfaces take place. For the first time, by means of theoretical calculations, the expediency and rationality of using the additional sources of heat such as high-temperature combustion product of solid-fuel gas generator based on sodium azide have been proved. Using of this additional source for the first 30 seconds of engine operation has been proved.
Practical value. Methodology of pressurization system parameters’ calculation was supplemented with discovered thermodynamic relation, which allowed us to calculate the amount of vapor and take some measures to eliminate the condensation. Results of the research allowed the designation of the pressurization system for the highly concentrated hydrogen peroxide tank with a high value of length to diameter relation with its high-temperature decomposition products.
|
Ключевые слова: condensation of the vapor, decomposition products, high temperature pressurization gas, high-test peroxide, pressurization system, saturated steam pressure |
References:
1. Andriievskyi M., Mitikov Y., Shamrovskyi D. (2017). Organization peculiarities of combustion chamber cooling of the rocket engine which runs on hydrogen peroxide. Aviatsionno-kosmicheskaya tehnika i tehnologiya, No. 5, 60—64 [in Russian].
2. A. s. 190290 SSSR, MKI F02k 11/00, B64D 37/24. Device for pressurizing the tank with hot gas. Yu. A. Mitikov, V. A. Moseiko, L. A. Ostashev. No. 2216292/23; declared 03.09.83; opubl. 09.05.83 [in Russian].
3. Belyaev N. M. (1976). Pressurization systems of the rockets’ tanks. Moscow: Mashinostroenie, 336 p. [in Russian].
4. Degtyarev A. V., Kushnarev A. P., Popov D. A. (2014). Small space launch vehicle. Kosmicheskaya tehnika. Raketnoe vooruzhenie, No. 1, 14—20 [in Russian].
5. de Selding P. B. (2016). SSTL Developing Non-toxic Thruster ahead of Possible European Hydrazine. Spacenews.
6. Hermsen R., Zandbergen B. Pressurization system for a cryogenic propellant tank in a pressure-fed high-altitude rocket. 7th Еuropean conference for aeronautics and aerospace sciences (EUCASS).
7. Jiachao Li, Guozhu Liang. (2019). Simulation of mass and heat transfer in liquid hydrogen tank during pressurization. Beijing: Beihang University, School of Asronautic.
8. Kim K. H., Ko H. J., Kim K., Jung, Y. S., Oh, S. H., Cho, K. J. (2012). Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization. J. Eng. Thermophys., No. 21(1), 1—15.
9. Manning T. A., Lawrence S. L. (2017). Fragment Acceleration Modeling for Pressurized Tank Burst. California: NASA Ames Research Center, Moffett Field.
https://doi.org/10.2514/1.A33765
10. Mitikov Y. (2015). Mathematical modeling of super cold pressurization system parameters for tank with kerosene. Aviatsionno-kosmicheskaya tehnika i tehnologiya, No. 5, 42—46 [in Russian].
10. Mitikov Y. (2015). Mathematical modeling of super cold pressurization system parameters for tank with kerosene. Aviatsionno-kosmicheskaya tehnika i tehnologiya, No. 5, 42—46 [in Russian].
11. Mitikov Y., Andriievskyi M. (2013). Modeling of the parameters of the oxygen pressurization system of a tank with kerosene. Aviatsionno-kosmicheskaya tehnika i tehnologiya, No. 1, 84—89 [in Russian].
12. Mitikov Yu. A., Antonov V. A., Voloshin M. L., Logvinenko A. I. (2012). Ways of the reliability and safety of missile systems operation improvement. Aviatsionno-kosmicheskaya tehnika i tehnologiya, No. 3(90), 30—36 [in Russian].
13. Patent of Ukraine No. 121267. IPC B64D 37/18, F02k 9/50. Mitikov Yu. O., Andrievsky M. V. How to pressurize the tank with storable oxidizer. No. a201806567 from 11.06.2018, opubl. 27.04.2020, Bul. 8.
14. Smirnov L. A., Silin V. S. (1993). Gunpowder, mixed solid fuels, pyrotechnic products and explosives for peaceful purposes. Ed. V. A. Zheltova. Moscow: TsNIINTIKP.
15. Ventura M., Mullens P. (1999). The Use of Hydrogen Peroxide for Propulsion and Power. AIAA. 2880.
16. Voit S. N., Serbin V. V., Mitikov Yu. A., Prisyazhny V. I., et al. (2018). History and commercialization of aerospace industry. Dnepr. Dominanta print, 88 p. [in Russian].
17. Wang L., Li Y., Li C., Zhao Z. (2013). CFD investigation of thermal and pressurization performance in LH2 tank during discharge. Cryogenics, No. 57, 63—73.