Search Results for “auger” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 05 Nov 2024 21:27:19 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “auger” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM https://journal.yuzhnoye.com/content_2024_1-en/annot_11_1_2024-en/ Mon, 17 Jun 2024 08:41:21 +0000 https://journal.yuzhnoye.com/?page_id=35014
2024, (1); 93-101 DOI: https://doi.org/10.33136/stma2024.01.093 Language: Ukrainian Annotation: The objective of this article is to develop a scientifically proven method of calculation of the auger conveyor parameters, such as the conveyor capacity and the corresponding power of the electrical motor, for different densities and porosities of conveyed materials, the geometrical parameters of the auger, and the specificity of the gravitational fields at the place of transportation. Another objective is to investigate potential limitations of the auger parameters when transporting lunar regolith. To reach these objectives, the known relations for calculating the auger conveyor parameters were applied, as well as the fundamental laws of the granular media mechanics, the principal equations of asynchronous motor electrodynamics, and the behavior of granular media when moving it with the auger conveyor, experimentally studied by the domestic authors.
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11. Parameters calculation of the lunar regolith transport system

Authors:

Semenenko Ye. V.1, Biliaiev M. M.2, Semenenko P. V.3

Organization:

National Academy of Sciences of Ukraine, M.S. Poliakov Institute of geotechnical mechanics1; Ukrainian State University of Science and Technologies2; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2024, (1); 93-101

DOI: https://doi.org/10.33136/stma2024.01.093

Language: Ukrainian

Annotation: The objective of this article is to develop a scientifically proven method of calculation of the auger conveyor parameters, such as the conveyor capacity and the corresponding power of the electrical motor, for different densities and porosities of conveyed materials, the geometrical parameters of the auger, and the specificity of the gravitational fields at the place of transportation. Another objective is to investigate potential limitations of the auger parameters when transporting lunar regolith. To reach these objectives, the known relations for calculating the auger conveyor parameters were applied, as well as the fundamental laws of the granular media mechanics, the principal equations of asynchronous motor electrodynamics, and the behavior of granular media when moving it with the auger conveyor, experimentally studied by the domestic authors. It gave the possibility, for the first time for the lunar environment, to suggest a procedure to calculate the auger conveyor parameters, such as the conveyor capacity and the corresponding power of the electric motor, using known geometrical parameters of the mainline and pipeline, the auger conveyor filling ratio and the parameters of the selected electrical motor. It gave the possibilities to study how the filling ratio of the auger conveyor influences its principal performance parameters and determine potential limitations of the geometrical parameters and the filling ratios of auger conveyors according to the parameters and features of the selected electrical motor. The allowable transportation distances, diameters, other geometrical parameters of auger conveyors, and conveyor filling ratios with the selected electrical motor have been determined. It has been proven that the solutions based on using auger conveyors would be most rational for transporting loose lunar regolith over the Moon’s surface because the auger conveyors are compact and adaptable, and they can be placed inside tubes and laid under the day surface, thereby ensuring the continuous transportation process. Furthermore, they are capable of autonomous operation and can use the electricity produced by solar arrays.

Key words: Moon, regolith, auger, electric motor, capacity, power

Bibliography:

1. Pustovgarov A. A., Osinoviy G. G. Kontseptsiya shlyuzovogo modulya misyachnoi bazy. ХХV Mizhnarodna molodizhna naukovo-praktychna conf. «Lyudyna i cosmos». Zbirnyk tez, NTsAOM, Dnipro, 2023. S. 86 – 87.
2. Semenenko P. V. Sposoby transortirovki poleznykh iskopaemykh ot mesta ikh dobychi k mestu pererabotki v lunnykh usloviyukh. P. V. Semenenko, D. G. Groshelev, G. G. Osinoviy, Ye. V. Semenenko, N. V. Osadchaya. XVII conf. molodykh vchenykh «Geotechnichni problemy rozrobky rodovysch». m. Dnipro, 24 zhovtnya 2019 r. S. 7.
3. Berdnik A. I. Mnogorazoviy lunniy lander. A. I. Berdnyk, M. D. Kalyapin, Yu. A. Lysenko, T. K. Bugaenko. Raketno-kosmichny complexy. 2019. T. 25. №5:3-10. ISSN 1561-8889. https://doi.org/10.15407/knit2019.05.003
4. Semenenko Ye. V., Osadchaya N. V. Traditsionnye i netraditsionnye vydy energii, a takzhe kosmicheskie poleznye iskopaemye v okolozemnom prostranstve. Nauch.-parakt. conf. «Sovremennye raschetno-experimentalnye metody opredeleniya characteristic raketno-kosmicheskoy techniki». m. Dnipro, 10 – 12 grudnya 2019 r. S. 62 – 63.
5. Komatsu pobudue excavator dlya roboty na Misyatsi https://www.autocentre.ua/ua/ news/concept/komatsu-postroit-ekskavator-dlya-raboty-na-lune-1380272.html.
6. Help NASA Design a Robot to Dig on the Moon https://www.nasa.gov/directorates/ stmd/help-nasa-design-a-robot-to-dig-on-the-moon/
7. Robert E. Grimm. Geophysical constaints on the lunar Procellarum KREEP Terrane. Vol. 118, Issue 4. April 2013. P. 768-778. https://agupubs-onlinelibrary-wiley-com.translate. goog/doi/10.1029/2012JE004114?_x_tr_sl=en&_x_tr_tl=ru&_x_tr_hl=ru&_x_tr_pto=sc
https://doi.org/10.1029/2012JE004114
8. Chen Li. A novel strategy to extract lunar mare KREEP-rich metal resources using a silicon collector. Kuixian Wei, Yang Li, Wenhui Ma, Yun Lei, Han Yu, Jianzhong Liu. Journal of Rare Earths Vol. 41, Issue 9, September 2023, P. 1429-1436. https://www-sciencedirect-com.translate.goog/science/article/ abs/pii/S1002072122001910?_x_tr_sl=en&_x_tr_tl=ru&_x_tr_hl=ru&_x_tr_pto=sc https://doi. org/10.1016/j.jre.2022.07.002
9. Moon Village Association https://moon-villageassociation.org/about/
10. GLOBAL MOON VILLAGE. https://space-architect.org/portfolio-item/ global-moon-village//
11. Just G. H. Parametric review of existing regolith excavation techniques for lunar In Situ Resource Utilization (ISRU) and recommendations for future excavation experiments. G. H. Just, Smith K., Joy K. H., Roy M. J. https://doi.org/10.1016/j.pss.2019.104746
https://www.sciencedirect.com/science/article/pii/S003206331930162X
12. Anthony J. Analysis of Lunar Regolith Thermal Energy Storage. Anthony J. Colozza Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio NASA Contractor Report 189073. November 1991. S-9 https://denning.atmos.colostate.edu/readings/ lunar.regolith.heat.transfer.pdf
13. Obgruntuvannya vykorystannya shneka dlya utilizatsii vidkhodiv vuglezbagachennya z mozhlyvistyu pidvyschennya bezpeki energetychnoi systemy pidpriemstv. SLobodyannikova I. L., Podolyak K. K., Tepla T. D. Materialy XХІ Mizhnarod. conf. molodykh vchennykh (26 zhovt. 2023 roku, m. Dnipro). Dnipro: IGTM im. M.S. Polyakova NAN Ukrainy, 2023. S. 50–55.
14. Kulikivskiy V. L., Paliychuk V. K., Borovskiy V. M. Doslidzhennya travmuvannya zerna gvintovym konveerom. Konstryuvannya, vyrobnitstvo ta exspluatatsiya silskogospodarskykh mashin. 2016. Vyp. 46. S. 160 – 165. https://doi.org/10.3233/EPL-46204
14. Lyubin M. V., Tokarchuk O. A., Yaropud V. M. Osoblyvosti roboty krutopokhylennykh gvyntovykh transporterov pri peremischenni zernovoi produktsii. Tekhnika, energetika, transport APK. 216. № 3(95). S. 235 – 240.
15. Gevko R. B., Vitroviy A. O., Pik A. I. Pidvyschennya tekhnichnogo rivnya gnuchkykh gvyntovykh konveeriv. Ternopil: Aston, 2012. 204 s.
16. Bulgakov B. M., Adamchyuk V. V., Nadikto V. T., Trokhanyak O. M. Teoretichne obgruntuvannya parametriv gnuchkogo gvintovogo konveera dlya transportuvannya zernovykh materialiv. Visnyk agrarnoi nauki. 2023. № 4(841). S. 59 – 66.
17. New Views of the moon. Reviews in mineralogy and geochemistry. Eds. Joliff B.L., Wieczorek M.A., Shearer C.K., Neal C.R. Mineralogical Society of America. Reviews in mineralogy and geochemistry. 2006. Vol. 60. 721 p. DOI: 10.2138/rmg.2006.60.
18. Semenenko Ye. V. Nauchnye osnovy technologiy hydromechanizatsii otkrytoy razrabotki titan-cyrkonovykh rossypey. Yevgeniy Vladimirovich Semenenko. Kiev: Nauk. dumka, 2011. 232 s.

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11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM
11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM
11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM

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]]> 9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps https://journal.yuzhnoye.com/content_2018_2-en/annot_9_2_2018-en/ Thu, 07 Sep 2023 11:25:59 +0000 https://journal.yuzhnoye.com/?page_id=30763
Cavitation Characteristics of High-Speed Auger-Centrifugal Pumps.
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9. The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps

Authors:

Nazarenko G. V., Filippenko P. P., Strelchenko O. Y., Deshevykh S. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 76-82

DOI: https://doi.org/10.33136/stma2018.02.076

Language: Russian

Annotation: In the present-day rocket engineering, the liquid rocket engines with pump feed system have gained wide acceptance. As a rule, the pumps used in liquid rocket engines are screw-axifugal. The screw serves to increase pressure upstream of the axifugal wheel, thus ensuring its cavitation-free operation. The screws used in the screw-axifugal pumps of liquid rocket engines may be of two types: with constant and variable step. The screws with constant step are easier to calculate, profile and manufacture as compared to the screws with variable step. As known from the literature, the use of the screw with variable step increases power characteristics of the screw-axifugal pump. The purpose of investigation is comparative analysis of cavitation and power characteristics of the following high-speed low-consumption screw-axifugal pumps of liquid rocket engines with jointed screws, screws of constant and variable step:  RD868 engine oxidizer and fuel pumps;  RD859 engine fuel pumps;  RD861K engine fuel pumps. Besides, the analysis has been made of the impact of design features and geometrical dimensions of the screws with variable and constant step on power characteristics of the screw-axifugal high-speed lowconsumption pumps of liquid rocket engines. Special attention has been given to the analysis of anticavitation properties of the pumps with screws of variable step and pumps with jointed screws. Based on the results of investigation, it has been ascertained that when using the joint screws and screws with variable step instead of the screws with constant step in the high-speed low-consumption screw-axifugal pumps of liquid rocket engines, the pump delivery head increases from 0.65 to 3.83%, the efficiency increases up to 1.7%. The use of jointed screw and screw of variable step as compared with the screw of constant step does not have any impact on cavitation properties of low-consumption crew-axifugal pumps of liquid rocket engines.

Key words: pressure characteristic, cavitation characteristic, inducers of the variable-pitch, continuous-pitch inducers, pump efficiency

Bibliography:
1. Pre-burner operating method for rocket turbopump: Patent 6505463 USA: MPK F02K9/48 / William D. Kruse, Thomas J. Mueller, John J. Weede (USA); Northrop Grumman Corporation. No. 20020148215; claimed 17.01.2001; published 14.01.2003, Bulletin No. 09/761,957. 5 p.
2. Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent: Patent 6640536 USA: MPK F02K9/50, F02K9/48, F02K9/46, F02K9/72, F02K9/56 / Korey R. Kline, Kevin W. Smith, Eric E. Schmidt, Thomas O. Bales; Hy Pat Corporation (Miami, FL). No. 20030136111; claimed 22.01.2002; published 04.11.2003, Bulletin No. 10/054,646. – 11 p.
3. Chebayevsky V. F., Petrov V. I. Cavitation Characteristics of High-Speed Auger-Centrifugal Pumps. М., 1973. 152 p.
4. Petrov V. I., Chebayevsky V. F. Cavitation on High-Speed Impeller Pumps. М., 1982. 192 p.
5. Ovsyanikov V. B., Borovsky B. I. Theory and Calculation of Liquid Rocket Engines Generator Sets. М, 1986. 376 p.
6. Borovsky B. I. Power Parameters and Characteristics of High-Speed Impeller Pumps. М., 1989. 181 p.

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9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps
9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps
9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps

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]]> 4.2.2018 Turbopump Units of Rocket Engines Developed by DO-4 https://journal.yuzhnoye.com/content_2018_2-en/annot_4_2_2018-en/ Thu, 07 Sep 2023 10:54:18 +0000 https://journal.yuzhnoye.com/?page_id=30735
Auger-Centrifugal Pump: Patent 73783, Ukraine: MPK 7F04D29/66 / Ivanov Y.
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4. Turbopump Units of Rocket Engines Developed by DO-4

Authors:

Ivanov Y. N., Badun O. P., Deshevykh S. O., Ivchenko L. F.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 25-33

DOI: https://doi.org/10.33136/stma2018.02.025

Language: Russian

Annotation: The article presents the experience of creating LRE turbopump units by the Rocket Engines Design Office (DO-4) at Yuzhnoye SDO. The best known turbopump units designs developed by DO are described. Both earlier developments of DO and the turbopump unit being now in final testing phase are considered. The design evolution of both separate assemblies and of entire unit is shown. The design evolution allowed increasing the unit’s lifetime dozens times. For example, the lifetime of the first turbopump units developed by DO did not exceed 150 s. Currently, the DO has in stock the engines with lifetime of ~19000 s. The information is presented on the problems that the designers faced in testing the turbopumop unit and the ways to solve them. The unique achievement are presented. At present, there are no analogs of some units in the world. The article presents the information on the latest achievements of DO, such as the face seal on pump vane discs whose use fully excludes unwanted leaks. Having analyzed the data presented, one may conclude that the Rocket Engines Design Office and Yuzhnoye SDO as a whole accumulated sufficient experience and knowledge allowing solving any problems that may arise when developing a new LRE turbopump unit, and successfully operating LRE with turbopump units, including those in the engines with generator gas afterburning created in recent years testify to a great value of accumulated experience.

Key words: liquid rocket engine, turbopump unit, pump, turbine

Bibliography:
1. Centrifugal Pump: Patent 1021816 А, USSR: MPK 7F04D1/00, 7F04D29/04 / Ivanov Y. N., Steblovtsev A. A.; Applicant and patent holder Yuzhnoye State Design Office. No. 3313928/25-06; claimed 06.07.1983, published 07.06.1984.
2. Auger-Centrifugal Pump: Patent 73783, Ukraine: MPK 7F04D29/66 / Ivanov Y. N., Pilipenko V. V., Zadontsev V. A., Drozd V. A.; Applicant and patent holder Yuzhnoye State Design Office. No. 2003021144; claimed 07.02.2003, published 15.09.2005.
3. End Seal. Patent 61082, Ukraine: MPK 7F16J15/34 / Ivanov Y. N., Chetverikova I. M.; Applicant and patent holder Yuzhnoye State Design Office. No. 990311536; claimed 19.03.1999, published 17.11.2003.
4. End Seal of High-Speed Shaft: Patent 48248, Ukraine: MPK F16J15/54, F04D29/10 / Ivanov Y. N., Steblovtsev A. A., Gameberger Y. A., Peredarenko V. M.; Applicant and patent holder Yuzhnoye State Design Office. No. 99031442; claimed 16.03.1999, published 15.08.2002.
5. Centrifugal Pump. Patent 84023, Ukraine: MPK F04D1/00 / Ivanov Y. N., Ivchenko L. F., Deshevykh S. A., Dan’kevich D. S.; Applicant and patent holder Yuzhnoye State Design Office. No. а200601399; claimed 13.02.2006, published 10.09.2008.

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4.2.2018 Turbopump Units of Rocket Engines Developed by DO-4
4.2.2018 Turbopump Units of Rocket Engines Developed by DO-4
4.2.2018 Turbopump Units of Rocket Engines Developed by DO-4

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