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Structural and technological diagram of a nitrogen cooling system of liquefied methane for refueling a medium-class launch vehicle

DOI: 10.17586/1606‑4313‑2020‑19‑4-27-36
UDC 66.045.7

Structural and technological diagram of a nitrogen cooling system of liquefied methane for refueling a medium-class launch vehicle

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. Structural and technological diagram of a nitrogen cooling system of liquefied methane for refueling a medium-class launch vehicle. Journal of International Academy of Refrigeration. 2020. No 4. p. 27–36. DOI: 10.17586/1606‑4313‑2020‑19‑4-27-36

Abstract
Based on the analysis of the preliminary modeling results for the cooling process of liquefied methane in straight-flow and counter-flow tubular heat exchangers, a rational variant of cooling liquefied methane for refueling a medium-class carrier rocket, implemented by a straight-flow heat exchanger, was selected from several options. For a more complete assessment of the processes occurring in the heat exchanger during nitrogen cooling of liquefied methane for the selected rational option, an in-depth simulation of the cooling process of liquefied methane was performed. A comparative analysis of the reliability of competing options for fundamental structural diagram of the nitrogen cooling of the liquefied methane, as a result of which the scheme comprising a nitrogen liquefier with centrifugal compressor and turboexpander of low pressure with booster compressor unit, storage and backup tanks with liquid nitrogen, and a ramjet heat exchanger - cooler of liquid methane was chosen as the base option, was carried out. The results of this work can be used in the design of nitrogen cooling systems of liquefied methane for refueling medium-class launch vehicles.

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

All references

1. Karpov A.B. Prospectsforusingliquefiednaturalgasasrocketenginefuel// Matera. IVall-RussianConf. "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. 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)

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

4. 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.

5. 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)

6. 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)

7. 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)

8. 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)

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

10. 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.

11. 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)

12. 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.

13. 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)

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

15. 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)

16. 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)

17. 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. (in Russian)

18. Smorodin A. I., Sergeev S. S., Kulik M. V., Korobkov A. A. Scientific and methodological apparatus for calculating the expander-compressor unit of the structural and technological scheme of an adsorption-cryogenic installation // Proceedings of the Institute of engineering physics. 2020. No. 3 (57). Pp. 2-9.(in Russian)

19. 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. (in Russian)

20. Hausen H. Heat transfer in counter-current, direct current and cross-current / TRANS. with him. I. N. Dulkina. M.: Energoizdat, 1981. 383 p.(in Russian)

21. Lavrov N.A. Mathematical modeling of low-temperature systems: textbook, Moscow: Bauman Moscow state technical University, 2016, 146 p.(in Russian)

22. Butkevich I.K. Quality and reliability of cryogenic systems. Moscow: Bauman Moscow State Technical University, 2007, 52 p.(in Russian)

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Structural and technological diagram of a nitrogen cooling system of liquefied methane for refueling a medium-class launch vehicle

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