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Comparative analysis of competing variants for the basic technological scheme of the liquefied methane cooling system for refueling the launch vehicle with underheated methane of increased density

DOI: 10.17586/1606‑4313‑2020‑19‑3-10-20
UDC 66.045.7

Comparative analysis of competing variants for the basic technological scheme of the liquefied methane cooling system for refueling the launch vehicle with underheated methane of increased density

Korobkov A.A., Kulik M.V., Red’kin V.V., Sergeev S.S., Smorodin A.I.

For citation: Korobkov A. A., Kulik M. V., Red’kin V. V., Sergeev S. S., Smorodin A. I. Comparative analysis of competing variants for the basic technological scheme of the liquefied methane cooling system for refueling the launch vehicle with underheated methane of increased density. Vestnik Mezhdunarodnoi akademii kholoda. 2020. No 3. p. 10–20.

Abstract
On the basis of known methods, installations and systems for cooling the carrier fuel components: oxygen and liquefied methane, a schematic diagram of a nitrogen system built on the basis of turbo-expander nitrogen liquefiers for cooling liquefied methane when refueling a medium-class carrier rocket has been developed. With the use of specialized software for modeling chemical processes (Aspen Hysys (v. 8.4)), mathematical modeling of schemes for competing variants and their elements was performed. The competing options are: – the scheme of a medium-capacity nitrogen liquefier with a nitrogen screw compressor and a low-pressure nitrogen turbo expander with an oil brake (scheme A); – the scheme of a medium-capacity nitrogen liquefier with a low-pressure nitrogen turbo expander with a booster compressor unit (scheme B). The comparison of competing variants for the basic technological scheme of the nitrogen cooling system for liquefied methane by the indicator-coefficient of nitrogen liquefaction (c) was made. The results of the work can be used in the design of nitrogen systems of liquefied methane cooling for refueling medium-class launch vehicles with under-heated high-density methane.

Keywords: nitrogen cooling system, rocket fuel components, mathematical modeling, methane, rocket and space technology, heat exchanger, turbo expander.

All references

1. Karpov A.B. Prospects for using liquefied natural gas as rocket engine fuel // Matera. IV all-Russian Conf. "Chemistry and chemical technology: achievements and prospects (November 27-28, 2018)". Moscow: Gubkin Russian State University of Oil and Gas, 2018.Pp. 408.1-408.3. (in Russian)

2. Energia Launch Vehicle (11K25) (Russia). [Electronic resource]: http://www.buran.ru/htm/rocket.htm. (in Russian)

3. Frolov S.M., Aksenov V.S., Ivanov V.S., Medvedev S.N. ets. Rocket engine with continuous detonation Gorenje fuel pair "natural gas-oxygen". Reports of the Academy of Sciences, Moscow: RAS, 2018, Vol. 478, No. 4, Pp. 429-433. (in Russian)

4. Yaczunenko G.S. Oxygen-methane rocket engines. Actual problems of aviation and cosmonautics. 2017. T 1. P. 209-210.(in Russian)

5. Nilsen C., Meriam S., Meyer S. Purdue Liquid Oxygen - Liquid Methane Sounding Rocket. American Institute of Aeronautics and Astronautics (AIAA). Session: Innovative Student Rocket Club Designs and Activities (7-11 January 2019). San Diego, California, 2019. doi: 10.2514/6.2019-0614.

6. Kalugin K.S., Suxanov A.V. Features of using methane as fuel for liquid rocket engines. Bulletin of the MAI. 2018. Vol. 25, No. 4. Pp. 120-132.(in Russian)

7. Bregvadze D.T., Gabidulin O.V., Gurkin A.A., Zabolot`ko I.A. Use of oxygen + methane fuel in liquid rocket engines. Polytechnic youth magazine. 2017. No. 12. Pp. 11-13.(in Russian)

8. Oreshkov M.A., Zlobin V.B. Design features of environmentally friendly liquid propellant upper stages. Actual problems of aviation and cosmonautics. 2017. T 1. Pp. 170-171.(in Russian)

9. Vasyanina A.Yu., Tonkix A.A., Savchin D.A., Ermolenko D.A. Prospects for using methane-oxygen fuel components in liquid rocket engines. Actual problems of aviation and cosmonautics. 2017. T 1. P. 121-123.(in Russian)

10. Roscosmos will create a rocket engine on methane. Transport on alternative fuel. 2016. no. 1 (49). Pp. 63-64.(in Russian)

11. Percy T., Polsgrove T., Alexander L., Turpin J. Design and Development of a Methane Cryogenic Propulsion Stage for Human Mars Exploration. American Institute of Aeronautics and Astronautics (AIAA). Session: In-Space Transportation (13-16 September 2016). Long Beach, California, 2016. doi: 10.2514/6.2016-5492.

12. State standard of the Russian Federation 56021-2014. Natural gas, liquefied. Fuel for internal combustion engines and power plants. Technical conditions. Introduced for the first time 2016-01-01. Moscow: standardinform, 2016. 13 p.(in Russian)

13. Ivanov A.I., Kosicyn I.P., Borisov V.A. Analysis of schematics of a low-thrust liquid-propellant rocket engine with a methane-powered aircraft turbopump. Bulletin of Samara University. Aerospace engineering, technologies and mechanical engineering. 2016. Vol. 15. No. 4. Pp. 75-80.(in Russian)

14. Chowdhury A., Cruz J., Aboud J., Rios A. ets. Design and Experimental Demonastration of a High Pressure Oxy-Methane Combustor. American Institute of Aeronautics and Astronautics (AIAA). Session: Terrestrial Energy Systems–Fuel Power Technologies (8-12 January 2018). Kissimmee, Florida, 2016. doi: 10.2514/6.2018-1476.

15. Aleksandrov A.A., Barmin I.V., Kunis I.D., Chugunkov V.V. Features of creation and development of cryogenic systems of Soyuz rocket and space launch complexes. Bulletin of the Bauman Moscow state technical University. Ser. «Engineering». 2016. No. 2. P. 7-27.(in Russian)

16. Director General of the Roscosmos state Corporation, Dmitry Rogozin, held a meeting on the progress of the Soyuz-5 RSC in Progress JSC (Russia). [Electronic resource]: https://www.samspace.ru/news/press_relizy/13380/.(in Russian)

17. RD0110MD, RD0162. Methane projects. Advanced reusable launch vehicles (Russia). [Electronic resource]: http://www.kbkha.ru/?p=8&cat=11&prod=59. (in Russian)

18. Red`kin V.V., Smorodin A.I., Sergeev S.S., Kulik M.V., Korobkov A.A. Competing variants of structural and technological schemes of nitrogen adsorption and cryogenic installations of cryothermic vacuum chambers for thermal vacuum tests of spacecraft. Proceedings of the Institute of engineering physics. 2020. no. 1 (55). Pp. 24-31.(in Russian)

19. Sajfullin A.D., Imaev A.M., Moiseev K.V. Determining the dependence of the coefficient of pair interaction on the temperature of the substance pairs "methane-heptane", "methane-nonan", "methane-octane", "methane-N-pentane", "methane-isopentane", "methane-hexane" for the Peng-Robinson equation of state. Alley of Science. 2017. Vol. 2 No. 10. Pp. 385-396.(in Russian)

20. Red`kin V.V., Smorodin A.I., Sergeev S.S., Kulik M.V., Korobkov A.A. Mathematical model and calculation method for heat exchange equipment of the basic version of the structural and technological scheme of the adsorption and cryogenic plant. Proceedings of the Institute of engineering physics. 2020. no. 2 (56). Pp. 25-32.

21. Antonov A.N., Arxarov A.M., Arxarov I.A. Rozenoer T.M. ets. Low-temperature machinery. Cryogenic machines and tools: textbook for universities; ed.by A. M. Arkharov and I. K. Butkevich. - 2nd ed., ISPR. M.: Publishing house of the Bauman Moscow state technical University, 2015. 536 p. (in Russian)

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