Search Results for “power” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Sun, 15 Mar 2026 16:16:09 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “power” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 12.2.2025 Algorithm for filling databases of the automated control system utilized at space rocketry enterprises, considering the differentiation of working and archived information. https://journal.yuzhnoye.com/content_2025_2-en/annot_12_2_2025-en/ Tue, 27 Jan 2026 09:26:33 +0000 https://journal.yuzhnoye.com/?page_id=35849
The implementation of this algorithm allows for promptly reducing the load on computing power and enhancing the fault resistance of computer systems.
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12. Algorithm for filling databases of the automated control system utilized at space rocketry enterprises, considering the differentiation of working and archived information.

Date of receipt of the article for publication: 29.09.2025

Date of acceptance of the article for publication after review: 13.10.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Manko T. A.1, Husarova I. O.2, Klymenko D. V.2

ORCID authors:

Manko T. A.1 ORCID, Husarova I. O.2 ORCID, Klymenko D. V.2 ORCID

Organization:

Oles Honchar Dnipro National University1, Yangel Yuzhnoye State Design Office2

Page: Kosm. teh. Raket. vooruž. 2025 (2); 105-111

DOI: https://doi.org/10.33136/stma2025.02.105

Language: Ukrainian

Annotation: The application of modern information technologies in enterprises of the rocket and space industry is an essential component for ensuring the high quality of economic activity. These technologies, such as the design of new systems and parts, the management of production cycles, the optimization of logistics operations, and the maintenance of fi nancial, economic, and accounting documentation, are actively integrated into the automation of various processes. This approach enables not only meeting modern market requirements and technological standards, but also achieving a signifi cant increase in the overall effi ciency of the enterprise. To increase the productivity of the automated control system (ACS) databases of Yuzhnoye State Design Offi ce and organize the disk space on servers through data archiving, the problems that arise when implementing the algorithm for fi lling ACS databases were investigated, taking into account the distinction between working and archival information in modern domestic enterprises, and recommendations were developed for resolving those problems. Approaches to devising a methodology for developing software based on a single database for enterprise management were improved, taking into account the requirements of enterprises in the rocket and space industry, by creating new programs that allow the application of modern information technologies. The practical signifi cance of the obtained results lies in the development of recommendations that can be used in the activities of Yuzhnoye State Design Offi ce and other enterprises. The warranty period for the servers and data storage systems at the enterprise has expired, which resulted in failures of a signifi cant amount of IT capacity. The implementation of this algorithm allows for promptly reducing the load on computing power and enhancing the fault resistance of computer systems. It will facilitate the process of making appropriate management decisions and ensure that management personnel are provided with relevant, targeted, complete, practical, and comparable information.

Key words: automation, rocket and space technology, programming, data processing, database, algorithm

Bibliography:

1. Ohorodnik M. i Zelinska O. Perevahy ta nedoliky reliatsiinykh ta nereliatsiinykh baz danykh. Prykladni aspekty suchasnykh mizhdystsyplinarnykh doslidzhen: materialy І Vseukr. nauk.-prakt. konf. (m. Vinnytsia, 26 lyst. 2021 r.), Vinnytsia, 2021. S. 106-108.
2. Dobrolubova M. V. Prohramuvannia baz danykh: konspect lektsii: navch. posib. dlia stud. spetsialnosti 152 «Metrologiia ta informatsiino-vymiriuvalna tekhnika». Kyiv: KPI im. Ihoria Sikorskoho, 2021. 275 s.
3. Dotsenko S. I. Orhanizatsiia ta systemy keruvannia bazamy danykh: Navch. posibnyk. Kharkiv: UkrDUZT, 2023. 117 s.
4. Zavadskyi I. O. Osnovy baz Danykh: Navch. posib. K. 2011. 192 s.
5. Ibraieva L. K. Proektirovanie baz danny’x. Konspekt lekcy’j dlya studentov vsex form obucheniya special’nosti 5В0702 – Avtomatizaciya i upravlenie. Almaty: AIES, 2010. 63 s.
6. Stvorennia povnoi rezervnoi kopii bazy danykh. URL: https://learn.microsoft.com/ru-ru/sql/relational-databases/backup-restore/create-a-full-database-backup-sql-server?view=sql-server-ver16&_gl=1*5hfglu*_gcl_au*MTUxMjE2NzIxOS4xNzMyNzMwNjMz (data zvernennia 29.11.24).
7. Vasilyeva E., Krupnov Yu. Development of the methodological approach to the comprehensive assessment of the innovative project effectiveness. E3S Web of Conferences. № 164, 2020, art.n. 10037. https://doi.org/10.1051/e3sconf/202016410037

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]]> 11.2.2025 Reviewing the benefits of utilizing AL–Mg–Sc alloys in Ukraine’s space rocket industry. Analysis of market factors https://journal.yuzhnoye.com/content_2025_2-en/annot_11_2_2025-en/ Tue, 27 Jan 2026 09:21:31 +0000 https://journal.yuzhnoye.com/?page_id=35846
The relevance and the scientifi c novelty of this study are determined by the need to fi nd new materials to replace traditional supplies, considering the aggravation of geopolitical confrontation (trade wars) between the PRC, USA, EU, Russian Federation, and other world powers in the markets of strategic raw materials.
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11. Reviewing the benefits of utilizing AL–Mg–Sc alloys in Ukraine’s space rocket industry. Analysis of market factors

Date of receipt of the article for publication: 03.11.2025

Date of acceptance of the article for publication after review: 17.11.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Yermolenko Ye. O.1, Mernikov H. I.1, Rudenko O. O.1, Bondarenko O. V.2

ORCID authors:

Bondarenko O. V.2 ORCID

Organization:

Yangel Yuzhnoye State Design Office1, Oles Honchar Dnipro National University2

Page: Kosm. teh. Raket. vooruž. 2025 (2); 93-104

DOI: https://doi.org/10.33136/stma2025.02.093

Language: Ukrainian

Annotation: The article outlines the prospects, possibilities, and directions for the space rocket applications of aluminumscandium alloys in Ukraine. It also analyzes the potential of Ukraine as a supplier of aluminum-scandium alloys. The relevance and the scientifi c novelty of this study are determined by the need to fi nd new materials to replace traditional supplies, considering the aggravation of geopolitical confrontation (trade wars) between the PRC, USA, EU, Russian Federation, and other world powers in the markets of strategic raw materials. As part of the search for alternative materials and sources of import for the manufacturing of space rocket technologies, this paper studies the possibilities of using aluminum alloys with enhanced properties, namely: Al–Mg, Al–Li, Al–Cu–Li, Al–Si–Mg, Al–Sc, and Al–Mg–Sc alloys. The paper demonstrates that the physical, mechanical, and chemical properties of aluminum-scandium and aluminum-magnesium-scandium alloys fi t the operating conditions of space rocket technologies. Moreover, these alloys have many advantages and allow for the enhancement of principal technical parameters for space rocket technologies, such as structural perfection (reduction of the mass of structures, high manufacturing accuracy due to the fi ne grain size of alloys), reliability of operation under severe conditions (high strength and resistance to vibration, heat, and corrosion), and the possibility of repeated use (heat resistance and durability of alloys). The manufacturing of parts from these alloys does not diff er from traditional production processes. Aluminum-scandium alloys are easy to weld, press, and machine by cutting. The paper corroborates that Ukraine holds the potential to revive its production of aluminum-scandium alloys, as it possesses a functioning research base and professionals. Ukraine’s mineral and feedstock base for scandium enables the country to satisfy any needs of the space rocket industry. Until 1995, Ukraine operated a plant producing scandium-containing alloys from Ukrainian raw materials. The resumption of production requires investment and political will.

Key words: aluminum-scandium alloys, space rocket technologies, market research, aluminum alloy manufacturers, price indicators

Bibliography:

1. Aluminii ta yoho spoluky v raketnii tekhnitsi. URL: https://evek.com.ua/reference/alyuminiy-i-ego-soedineniya-v-raketnoy-tehnike.html (data zvernennia 21.09.2025).
2. 5000 Series Aluminum Alloy: A Comprehensive Overview. URL: https://elkamehr.com/en/5000-series-aluminum-alloy/ (data zvernennia 21.09.2025).
3. Aluminii, mid ta splavy na yikh osnovi. NUBiP Ukrainy. pdf URL: https://elearn.nubip.edu.ua/pluginfile.php/704375/mod_resource/content/2/%D0%9C%D0%BE%D0%B4_2_%D0%9B%D0%B5%D0%BA%D1%86i%D1%8F_11_%D0%B0%D0%BB%D1%8E%D0%BCi%D0%BDi%D0%B9_%D0%BCi%D0%B4_.pdf?utm_source=chatgpt.com (data zvernennia 21.09.2025).
4. Dzhur Ye. O., Kalinina N. Ye., Dzhur O. Ye., Kalinin O. V., Nosova T. V., Mamchur S. I. Pidvyshchennia vlastyvostei deformovanykh aluminiievykh splaviv, modyfikovanykh nanokompozytsiiamy. Kosmichna nauka i technolohiia. 2021. 27, № 6 (133). S. 98—104. https://doi.org/10.15407/knit2021.06.098
5. Kalinina N. Ye., Bondarenko O.V. Vykorystannia aluminiievykh splaviv v aviatsiinii ta raketno-kosmichnii tekhnitsi: Navch. posib. D.: RVV DNU, 2011. 64 s.
6. Davyduk A., Polizhko S. Zmina struktury ta mekhanichnykh vlastyvostei aluminiievoho splavu systemy Al–Mg–Sc unaslidok obroblennia kompleksnym nanomodyfikatorom. Visn. Kharkivskoho natsionalnoho avtomobilno-dorozhnoho universytetu. 2023. № 103. S. 211–215.
7. Ostash O. P., Chepil R. V., Titov V. A., Polivoda S. L., Voron M. M., Podhurska V. Ya. Mitsnist i tsyklichna trishchinostiikist termodeformovanykh splaviv systemy Al–Mg–Sc. Fizyko-khimichna mekhanika materialiv. 2021. T. 57. № 3. S. 118-125. https://doi.org/10.1007/s11003-021-00555-w
8. AIAA Propulsion and Energy Forum, 2019 — Additive Manufacturing for Propulsion Systems, 19–22 august 2019. S. 217.
9. Perestan’ gry’zt’ vafli, rozdil «Kosmonavtyka» saitu N+1, 2021 r. URL: https://ru.wikipedia.org/wiki/%D0%A1%D0%BA%D0%B0%D0%BD%D0%B4%D0%B8%D0%B
10. Scandium oxide is a rare and valuable metal. URL: https://ua.hnosc.com/news/scandium-oxide-is-a-rare-and-valuable-metal-th-75876554.html
11. Aluminum Market Size, Share, and Trends 2025 to 2034. URL: https://www.precedenceresearch.com/aluminum-market (data zvernennia 21.09.2025).
12. Aluminium Market Size, Share & Industry Analysis, By Product (Sheet, Plate, Cast Products, Extrusion, and Others), By Alloy Type (Cast Alloy and Wrought Alloy), By End-use (Construction, Transportation {Aerospace, Automotive, and Marine}, Packaging {Food & Beverages, Cosmetics, and Others}, Electrical, Consumer Durables, Machinery & Equipment, and Others), and Regional Forecast, 2024-2032. 2025. URL: https://www.fortunebusinessinsights.com/industry-reports/aluminium-market-100233 (data zvernennia 21.09.2025).
13. Global Market Insights, Inc. Aluminum Alloys Market Size By Product (Wrought, Cast), By End-user (Transportation, Construction, Packaging, Machinery, Electrical): Industry Analysis Report, Regional Outlook, Growth Potential, Price Trends, Competitive Market Share & Forecast, 2017–2024. April 2017.
URL: https://www.gminsights.com/industry-analysis/aluminum-alloys-market
14. Aluminum Scandium Alloys Market Size. 2025. https://www.globalgrowthinsights.com/market-reports/aluminum-scandium-alloys-market-107081 (data zvernennia 21.09.2025).
15. Аluminium scandium alloy market. 2025. https://market.us/report/aluminium-scandium-alloy-market/ (data zvernennia 21.09.2025).
16. Aluminum Producing Companies in the World, 6 august 2020.
URL: https://www.steeltechnology.com/articles/aluminum-producing-companies-in-the-world?utm_source=chatgpt.com
17. Miningdigital URL: https://miningdigital.com/top10/top-10-aluminium-mining-processing-companies?utm_source=chatgpt.com
18. Geopolitical Impact Analysis https://market.us/report/aluminium-scandium-alloy-market/ (data zvernennia 21.09.2025).

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]]> 7.2.2025 Autonomous deployable landing interface: a detailed technical framework for Mitigating terminal descent risks on planetary surfaces https://journal.yuzhnoye.com/content_2025_2-en/annot_7_2_2025-en/ Tue, 27 Jan 2026 08:45:39 +0000 https://journal.yuzhnoye.com/?page_id=35834
Specifi c focus is given to the proposed solutions for electromagnetic compatibility (EMC); the power nfrastructure required for high-voltage electrostatic systems; the system’s structural and mechanical reliability through the use of solid-state actuators and robust materials; and the strategic costbenefi t of lander mass reduction enabled by this infrastructure.
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7. Autonomous deployable landing interface: a detailed technical framework for Mitigating terminal descent risks on planetary surfaces

Date of receipt of the article for publication: 03.11.2025

Date of acceptance of the article for publication after review: 17.11.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Автори: Iteba A. K., Weramundi N. E.

Organization: University of Nairobi

Page: Kosm. teh. Raket. vooruž. 2025 (2); 67-70

DOI: https://doi.org/10.33136/stma2025.02.067

Language: English

Annotation: The terminal descent phase of landing is a mission-critical failure point for all planetary surface exploration. This paper presents a detailed technical framework for the Lunar Landing Interface (LLI), a deployable, autonomous ground structure designed to create a controlled environment that mitigates these universal risks. We provide an in-depth analysis of the material science, component design, and operational principles of the LLI. Specifi c focus is given to the proposed solutions for electromagnetic compatibility (EMC); the power nfrastructure required for high-voltage electrostatic systems; the system’s structural and mechanical reliability through the use of solid-state actuators and robust materials; and the strategic costbenefi t of lander mass reduction enabled by this infrastructure. The scientifi c novelty of this work lies in the integrated systems approach, combining origami-inspired deployment with active dust mitigation and ground-based autonomous guidance to solve the terminal descent problem holistically. The practical signifi cance is a clear path toward reducing the cost and increasing the safety of lunar access, thereby enabling a sustainable lunar economy. This work expands upon a preliminary concept to provide the detailed theoretical and engineering rationale necessary to prove the LLI’s feasibility and justify further investment in its development, directly addressing reviewer feedback

Key words: Lunar Landing, Terminal Descent, Dust Mitigation, Origami Structures, Autonomous Systems, Spacecraft Design, Regolith, ShapeMemory Alloys

Bibliography:

1. Mike Wall. Intuitive machines’ private athena probe lands near lunar south pole – but it may have tipped over, 20.
2. NASA Science. Beresheet, 2019.
3. KYODO NEWS. Japan ispace fails in bid for 1 st moon landing by asian private firm, 2025.
4. Thornton Bryce, Ireland Tom. The economics of reusable launch vechicles. New Space. 10(2). 125-135, 2022.
5. Attard M., Chirima G., Kar-Eng K. A review of the applications of indium tin oxide (ito). Journal of Physics: Conference Series, 2071:012001, 2021.
6. Shaw J.A., Grummon D.S., Folias S. Shape memory alloy applications in aerospace. Progress in Aerospace Sciences, 126:100743, 2021.
7. Sternovsky Z., Szalay J.R., Horányi M., Drake E. Photoelectric charding and transport of lunar dust. Journal of Geophysical Research: Planets. 128 (5), 2023.

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]]> 5.2.2025 Analysis and minimization of resistive forces occurring during rocket stage separation. Possibility of using a single pneumatic pusher for stage separation https://journal.yuzhnoye.com/content_2025_2-en/annot_5_2_2025-en/ Tue, 27 Jan 2026 08:28:58 +0000 https://journal.yuzhnoye.com/?page_id=35828
For the fi rst time in the practice of launch vehicle design, the authors present a separation system that eliminates resistive forces through the use of an alternative complex of electrical disconnectors, featuring noncontact data transfer and allowing for reduced power losses and fewer elements that produce relative speed for the stage separation system, resulting in a signifi cantly lighter overall mass of the system.
]]>

5. Analysis and minimization of resistive forces occurring during rocket stage separation. Possibility of using a single pneumatic pusher for stage separation

Date of receipt of the article for publication: 10.11.2025

Date of acceptance of the article for publication after review: 24.11.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Udovychenko D. O., Makarenko A. O.

ORCID authors:

Udovychenko D. O. ORCID

Organization:

Yangel Yuzhnoye State Design Office

Page: Kosm. teh. Raket. vooruž. 2025 (2); 46-57

DOI: https://doi.org/10.33136/stma2025.02.046

Language: Ukrainian

Annotation: One of the primary objectives in designing separation systems for rocket stages is to create a system featuring minimal mass while ensuring the required relative speed of stage separation, achieving minimal thrust diff erence, and preventing contamination of spacecraft surfaces. Based on the results of resolving an optimization problem, the utilization of one pneumatic pusher for stage separation is one of the optimum scenarios, which will enable a several times lighter mass of the separation system due to the signifi cant reduction of the mass of pipelines, the overall mass of the pusher, and the mass of gas bottles and their fasteners. The preliminary analysis of the separation process and the possibility of using a single pneumatic pusher for stage separation was performed using a mathematical model in the form of a system of diff erential equations describing the stage separation process, and through a series of calculations. The calculation results demonstrate that using a single pneumatic pusher to minimize the risk of an emergency requires a substantial reduction of the resistive forces occurring during stage separation. The article reviews the results of ground development testing for the stage separation system utilized in the Cyclone launch vehicles. It simulates an emergency when an abnormal detachment of the structural elements of stages occurs due to a meshing of electrical disconnector covers, resulting in the adapter section rotation by an angle over the allowable value. The article outlines the method for the experimental determination of resistive forces, presents calculated values obtained during the design phase, and compares these values with experimental data. Resistive force components were identifi ed during testing, such as detachment forces for electrical connectors and sealing elements, and friction forces in guiding studs. For the fi rst time in the practice of launch vehicle design, the authors present a separation system that eliminates resistive forces through the use of an alternative complex of electrical disconnectors, featuring noncontact data transfer and allowing for reduced power losses and fewer elements that produce relative speed for the stage separation system, resulting in a signifi cantly lighter overall mass of the system. The article analyzes resistive forces induced by the detachment of sealants. It presents a procedure for the autonomous development testing of joint sealants, which identifi es the relation between their detachment force and layer thickness. A technique for sealant application to the attachment surface has been developed. The test results enabled determining the required thickness of attachment sealants and the optimum application technique. Therefore, the change in the sealant application technique resulted in a 2.3 times lower maximum resistive force during stage separation, which meets the maximum and design values. The results of experiments provide meaningful data for the engineers of stage and booster separation systems for spacecraft and launch vehicles. Furthermore, they confi rm the feasibility of using alternative electrical disconnectors for stage separation.

Key words: pneumatic pusher, non-contact electric connector, resistive force, stage separation system, minimum mass of the stage separation system, emergencies, transient dynamics, launch vehicle, materials properties, strength

Bibliography:

1. Hamand M. Yehia, Rigid body dynamics: A Lagrangian Approach. Boston, Birkhauser. 2022. 485 p.
2. Ahmed A. Shabana, Dinamic of Multibody Systems. Cambridge, Cambridge University Press. 2020. 420 p.
3. Beiko I. V., Bublyk B. M., Zinko P. M. Metody i alhorytmy rozviazannia zadach optymizatsii. Kyiv: Vyshcha shkola. 1983. 512 s.
4. Udovychenko D. O. Optymizatsiia parametriv pnevmatychnoi systemy rozdilennia stupeniv rakety-nosiia kosmichnoho pryznachennia. Visnyk DNU. 2025. 34 (3). S. 9-17.
5. Linnyk A. K. Konstruiuvannia korpusiv ridynnykh balistychnykh raket. Dnipro, Vyd-vo DDU. 1994. 220 s.
6. Joaquim A. Battle, Anna Barjam Condomines, Rigid body dynamics, Cambridge, Cambridge University Press. 2022. 596 p.

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]]> 2.2.2025 Performance analysis and validation of a monopropellant air-detonation ramjet engine https://journal.yuzhnoye.com/content_2025_2-en/annot_2_2_2025-en/ Tue, 27 Jan 2026 08:06:29 +0000 https://journal.yuzhnoye.com/?page_id=35818
Development of a liquid-propellant rocket powered by a rotating detonation engine. Journal of Propulsion and Power. Journal of Propulsion and Power. Journal of Propulsion and Power.
]]>

2. Performance analysis and validation of a monopropellant air-detonation ramjet engine

Date of receipt of the article for publication: 15.10.2025

Date of acceptance of the article for publication after review: 29.10.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Stoliarchuk V. V., Tertyshnyk S. V.

ORCID authors:

Stoliarchuk V. V. ORCID, Tertyshnyk S. V. ORCID

Organization:

Page: Kosm. teh. Raket. vooruž. 2025 (2); 12-23

DOI: https://doi.org/10.33136/stma2025.02.012

Language: English

Annotation: The increasing relevance of alternative propulsion systems necessitates an exploration of the potential of monopropellant detonation engines for compact and effi cient aerospace applications. This study aimed to investigate the operating parameters and performance characteristics of a direct-fl ow air-detonation propulsion system operating on environmentally friendly monopropellants. The research was based on a combination of experimental methods and numerical simulation using validated thermochemical models. It presents the results of a series of tests conducted with modifi ed engine geometries under varying inlet temperature and pressure conditions, focusing on achieving a stable detonation wave and analysing its propagation features. A detailed comparison between experimental pressure data and numerical predictions showed a deviation of less than 6.5 %, validating the reliability of the simulation model for practical applications. The infl uence of diff erent combustion chamber lengths and injector confi gurations was also assessed, revealing that geometric optimization plays a crucial role in maintaining detonation stability across diff erent temperature regimes. The study identifi ed critical fl ow parameters for successful ignition and detonation maintenance without external oxidizers, and highlighted the performance of two promising monopropellant compositions, including a modifi ed pronit-based propellant. The fi ndings contribute to optimizing heat release dynamics and pressure gain within the detonation chamber, off ering valuable insights into designing lightweight, energy-effi cient engines for future aerospace systems. The practical value of this research lies in the potential of applying its results in the design of advanced aerospace propulsion systems that feature compact size and environmental friendliness.

Key words: detonation combustion, wave stability, experimental simulation, thermal dynamics, geometric optimisation

Bibliography:

1. Zhang H., Jiang L., Liu W. D. & Liu S. J. Characteristic of rotating detonation wave in an H2/Air hollow chamber with Laval nozzle. International Journal of Hydrogen Energy. 2021. 46 (24). 13389–13401. https://doi.org/10.1016/j.ijhydene.2021.01.143
2. Xue S., Ying Z., Hu M., & Zhou C. Experimental study on the rotating detonation engine based on a gas mixture. Frontiers in Energy Research. 2023. 11. 1136156. https://doi.org/10.3389/fenrg.2023.1136156
3. Xue S., Ying Z., Ma H., & Zhou C. Experimental investigation on two-phase rotating detonation fueled by kerosene in a hollow directed combustor. Frontiers in Energy Research. 2022. 10, 951177. https://doi.org/10.3389/fenrg.2022.951177
4. Kawalec M., Wolanski P., Perkowski W., & Bilar A. Development of a liquid-propellant rocket powered by a rotating detonation engine. Journal of Propulsion and Power. 2023. 39(4). 554–561. https://doi.org/10.2514/1.B38771
5. Zolotko O. Y., Zolotko O. V., Aksyonov O. S., Stoliarchuk V. V., & Cherniavskyi O. S. Analysis of the characteristics of the ejector regime of the impulse-detonation engine of the combined cycle of acceleration. Aerospace technic and technology. 2024. 6 (200). 52–59. https://doi.org/10.32620/aktt.2024.6.05
6. Camacho, R. G., & Huang, C. Component-based reduced order modelling of two-dimensional rotating detonation engine with non-uniform injection. AIAA SCITECH 2025 Forum.
https://doi.org/10.2514/6.2025-1397
7. Feng W., Zhang Q., Xiao Q., Meng H., Han X., Cao Q., Huang H., Wu B., Xu H., & Weng C. Effects of cavity length on operating characteristics of a ramjet rotating detonation enjine fueled by liquid kerosene. Fuel. 2023. 332. 126129. https://doi.org/10.1016/j.fuel.2022.126129
8. Bennewitz J. W., Bigler B. R., Ross M. C., Danczyk S. A., Hargus W. A. Jr. & Smith R. D. Performance of a rotating detonation rocket engine with various convergent nozzles and chamber lengths. Energies. 2021. 14(8). 2037. https://doi.org/10.3390/en14082037
9. Curran D., Wheatley V. & Smart M. High Mach number operation of accelerator scramjet engine. Journal of Spacecraft and Rockets. 2023. 60(3). https://doi.org/10.2514/1.A35511
10. Sun D., Dai Q., Chai W. S., Fang W. & Meng H. Experimental studies on parametric effects and reaction mechanisms in electrolytic decomposition and ignition of HAN solutions. ACS Omega. 2022. 7(22). 18521–18530. https://doi.org/10.1021/acsomega.2c01183
11. Stoliarchuk V. V. Validation of efficiency enhancement methods for detonation jet engines. Aerospace technic and technology. 2024. 4(1). 82–88. https://doi.org/10.32620/aktt.2024.4sup1.12
12. Wang J., Liu Y., Huang W., Zhang Y. & Qiu H. Direct numerical simulation of inflow boundary-layer turbulence effects on cavity flame stabilisation in a model scramjet combustor. Aerospace Science and Technology. 2025. 165. 110463. https://doi.org/10.1016/j.ast.2025.110463
13. Li W., Oh H. & Ladeinde F. Comparison of flamelet and transported species-based modeling of rotating detonation engines. AIAA SCITECH 2024 Forum. https://doi.org/10.2514/6.2024-2599.
14. Chen Y., Liu S., Peng H., Zhong S., Zhang H., Yuan X., Fan W. & Liu W. Propagation and heat release characteristics of rotating detonation in a ramjet engine with a divergent combustor. Physics of Fluids, 2025 37(2), 026132. https://doi.org/10.1063/5.0254419
15. Kailasanath K. Review of propulsion applications of detonation waves. AIAA Journal. 2000. 38(9). 1698–1708. https://doi.org/ 10.2514/2.1156
16. Heiser W. H., & Pratt D. T. Thermodynamic cycle analysis of pulse detonation engines. Journal of Propulsion and Power. 2002. 18(1), 68–76. https://doi.org/10.2514/2.5899
17. Munipalli R., Shankar V., Wilson D. R., Kim H., Lu F. K. & Liston G. Performance assessment of ejector-augmented pulsed detonation rockets. In 39th Aerospace Sciences Meeting and Exhibit (Paper 2001-0830). Reno: AIAA. https://doi.org/10.2514/6.2001-830
18. Lu F. K. & Braun E. M. Rotating detonation wave propulsion: Experimental challenges, modeling, and engine concepts. Journal of Propulsion and Power. 2014. 30(5). 1125–1142. https://doi.org/10.2514/1.B34802
19. Armbruster W. et al. Design and testing of a hydrogen–oxygen pre-detonator for RDEs. CEAS Space Journal. 2025. 17. 969-979.
https://doi.org/10.1007/s12567-025-00605-y

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]]> 1.1.2025 Promomoon initiative for moon village generation in honor of dr. Alexander degtyarev https://journal.yuzhnoye.com/content_2025_1-en/annot_1_1_2025-en/ Sun, 25 Jan 2026 23:53:07 +0000 https://journal.yuzhnoye.com/?page_id=35475
The Lunar-Based Solar Power Station with Microwave Power Transmission from a Satellite Orbiter was developed by the Lunar Energizers team, and the Lunar Regolith-Based ThermalEnergy Storage for Moon Village Generation, in the project of the same name. Project Lunar-based Solar Power Station with Microwave Power Transmission Satellite Orbiter.
]]>

1. Promomoon initiative for moon village generation in honor of dr. Alexander degtyarev

ISSN: 2617-5525

e-ISSN: 2617-5533

Автори: Degtiarov M. O., Gusarova I. O., Osynovyy G. G.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2025 (1); 3-10

DOI: https://doi.org/10.33136/stma2025.01.003

Language: English

Annotation: Moon Village Association, together with Yuzhnoye State Design Offi ce, created and implemented the Mentorship Program “PromoMoon Initiative for Moon Village Generation in honor of Dr. Alexander Degtyarev ˮ. The main goal of the Program is to build the capacity of new participants in the space market. The Mentorship Program allows the winners of the competition to receive expert assessment through online B2B mentorship sessions provided by MVA members and specialists from Yuzhnoye State Design Offi ce. This year marks the 4th PromoMoon Initiative. 19 projects are presented by participants from 16 countries. Most of the projects are dedicated to the creation of lunar base infrastructure and technologies for extracting useful resources on the Moon. The main focus of the proposed projects is on the use of local resources, cost-eff ectiveness and reliability. Seven projects are dedicated to various residential module designs: with an infl atable chamber and high-strength shells; with small 3D-printed panels and their assembly in a module; modular habitats created and serviced by autonomous microrobots; modules using biomimetic principles of adaptation found in Earth’s natural systems. The modules are made of terrestrial materials, lunar regolith, and a building material based on radiation-absorbing fungi, as well as “PotatoCreteˮ material derived from potato raw materials. The Lunar-Based Solar Power Station with Microwave Power Transmission from a Satellite Orbiter was developed by the Lunar Energizers team, and the Lunar Regolith-Based ThermalEnergy Storage for Moon Village Generation, in the project of the same name. The Tochtli system for regolith extraction and processing was proposed by the Torres Orbital Mining team, the RegOne system for regolith extraction and transportation was proposed by the MoonAixperts e.V. team. Anodes for direct molten regolith electrolysis were developed by a team of Ukrainian scientists. The Sand to Green team developed a lunar agroforestry system. Two launch complexes, the Lunar Electrostatic Dust Removal Station, a lunar rescue sled and a centralized cloud platform with open access for storing, analyzing and exchanging lunar mission data were proposed.

Key words: lunar modules, local resources, extraction of useful resources

Bibliography:

1. Project Oxygen Space. URL: https://moonvillageassociation.org/announcement-4th-promomoon-intiative.

2. Project Moon Arc / M.S.C.A.P.E. URL: https://moonvillageassociation.org/ announcement-4th-promomoon-intiative.

3. Project Lunar Metropolis: 3D-Printed Modular Habitat. URL: https://moonvillageassociation.org/ announcement-4th-promomoon-intiative.

4. Project Pine flex lunar biome. URL: https://moonvillageassociation.org/ announcement-4th-promomoon-intiative.

5. Project Lunar-based Solar Power Station with Microwave Power Transmission Satellite Orbiter. URL: https://moonvillageassociation.org/ announcement-4th-promomoon-
intiative.

6. Project TOM’s Tochtli and Lunar regolith excavation. URL: https://moonvillageassociation.org/ announcement-4th-promomoon-intiative.

7. Project URL: https://moonvillageassociation.org/ announcement-4th-promomoon-intiative.

8. O.N. Grigoriev, I.P. Neshpor, T.V. Mosina, V.B. Vinokurov, A.V. Koroteev, O.V. Buriachek, D.V. Vedel, A.N. Stepanchuk, L. Silvestroni, Behavior of Ultrahigh
Temperature ZrB2-Based Ceramics in Oxidation. Powder Metallurgy and Metal Ceramics. 2018. № 56.573-580 р. DOI: https://doi.org/10.1007/s11106-018-9930

9. D.Vedel, O.Grigoriev, P.Mazur, A.Osipov, M.Brodnikovskyi, L.Silvestroni, Effect of Mo2C addition on the mechanical properties and oxidation resistance of ZrB2-SiC
ceramics. Journal of Alloys and Compounds. 2021. V. 879. P. 160398 DOI: https://doi.org/10.1016/j.jallcom.2021.160398.

10. Gusarova I. O., Lysenko Yu. O., Osinovyy G.G., Future projects of lunar exploration implemented by Yuzhnoye SDO. Space technology. Missile armaments, 2024, № 1
(121). P. 19-28. https://doi.org/10.33136/stma2024.01.019

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]]> 2.1.2025 Justification of the parameters of a vertical screw conveyor for transporting lunar regolith https://journal.yuzhnoye.com/content_2025_1-en/annot_2_1_2025-en/ Wed, 27 Aug 2025 12:20:10 +0000 https://journal.yuzhnoye.com/?page_id=35479
2025 (1); 11-18 DOI: https://doi.org/10.33136/stma2025.01.011 Language: Ukrainian Annotation: This paper aims to develop a scientifi cally grounded method for determining the key technical parameters of a vertical screw conveyor–specifi cally, throughput and the power requirement of the driving electric motor. These systems are compact, adaptable, capable of integration within tubes or underground installations, operate continuously, function autonomously, and can be powered by solar energy. Key words: Moon , regolith , screw conveyor , electric motor , throughput , power Bibliography: 1. Development of a sustainable portable Archimedes screw turbine for hydropower generation. A power loss model for Archimedes screw generators. Moon , regolith , screw conveyor , electric motor , throughput , power .
]]>

2. Justification of the parameters of a vertical screw conveyor for transporting lunar regolith

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Semenenko Ye. V.2, Semenenco P. V.1

Organization:

National Academy of Sciences of Ukraine, M. S. Poliakov Institute of geotechnical mechanics2, Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1

Page: Kosm. teh. Raket. vooruž. 2025 (1); 11-18

DOI: https://doi.org/10.33136/stma2025.01.011

Language: Ukrainian

Annotation: This paper aims to develop a scientifi cally grounded method for determining the key technical parameters of a vertical screw conveyor–specifi cally, throughput and the power requirement of the driving electric motor. These parameters depend on the density and porosity of the transported material, the screw’s geometric characteristics, and the gravitational fi eld at the transportation site. The study also explores potential design constraints when handling lunar regolith. To achieve this objective, the authors applied established equations for screw conveyor parameter calculations, fundamental principles of bulk material mechanics, key electrodynamic equations for asynchronous motors, and specifi c behavioral characteristics of bulk materials during vertical screw transport, which were also investigated experimentally. As a result, a novel method is proposed for calculating the technical specifi cations of a screw conveyor under lunar conditions, based on known geometric parameters, fi lling ratio, and electric motor characteristics. The study further examines the infl uence of the conveyor’s fi lling ratio on performance and identifi es geometric limitations imposed by the operational boundaries of the selected motor. Acceptable values for transport height, screw diameter, other geometric parameters, and achievable fi lling ratios for a given motor are determined. The study substantiates that vertical screw conveyors are the most promising solution for lunar regolith transport. These systems are compact, adaptable, capable of integration within tubes or underground installations, operate continuously, function autonomously, and can be powered by solar energy.

Key words: Moon, regolith, screw conveyor, electric motor, throughput, power

Bibliography:

1. Semеnenko Ye. V., Osadchaia N. V. Traditsionnyie i netraditsionnyie vidy energii, a takzhe kosmicheskiie poleznyie iskopaiemyie v okolozemnom prostranstve.
Nauchno-prakticheskaia konferentsiia «Sovremennyie raschetno-eksperimentalnyie metody opredeleniia kharakteristik raketno-kosmicheskoi techniki». m. Dnipro, 10 12 hrudnia 2019 r. S. 62 – 63. https://doi.org/10.1016/j.repl.2019.01.038

2. Jolliff B. L., Wieczorek M. A., Shearer C. K., Neal C. R. New Views of the Moon. Reviews in mineralogy and geochemistry. 2006. Vol. 60. 721 p. DOI: https://doi.org/10.2138/rmg.2006.60.0

3. Robert E. Grimm. Geophysical constaints on the lunar Procellarum KREEP Terrane. Journal of Geophysical Research: Planets. 2013. Vol. 118, Issue 4. P. 768-778. URL: 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

4. Moon Village Association. URL: https://moon-villageassociation.org/about/

5. GLOBAL MOON VILLAGE. URL: https://space-architect.org/portfolio-item/ global-moon-village

6. Pustovharov А. А., Osynovyy G. G. Kontseptsiia shluzovogo modulia misiachnoi bazy. ХХV Mizhnarodna molodizhna naukovo-praktychna konferentsiia «Ludyna i kosmos».
Zbirnyk tez, NTSAOM, Dnipro, 2023. S. 86 – 87.

7. Berdnik A. I., Kaliapin M. D., Lysenko Yu. A., Bugaienko T. K. Mnogorazovyi lunnyi lender. Kosmichna nauka i technologiia. 2019. T. 25. № 5. S. 3-10.
https://doi.org/10.15407/knit2019.05.003

8. Semenenko P. V. , Groshelev D. G., Osinovyy G. G., Semenenko Ye. V., Osadchaia N. V. Sposoby transportirovki poleznykh iskopaiemykh ot mesta ikh dobychi k mestu pererabotki v lunnykh usloviiakh. XVII konferentsiia molodykh vchenykh «Heotekhnichni problemy rozrobky rodovyshch». m. Dnipro, 24 zhovtnia 2019 r. S 7.

9. Komatsu pobuduie ekskavator dlia roboty na Misiatsi. URL: https://www.autocentre.ua/ua/ news/concept/komatsu-postroit-ekskavator-dlya-raboty-na-lune-1380272.html.

10. Help NASA Design a Robot to Dig on the Moon. URL: https://www.nasa.gov/directorates/ stmd/help-nasa-design-a-robot-to-dig-on-the-moon/

11. Semenenko Ye. V. , Semenenko P. V., Hroshelev D. H. Tekhnolohichni parametry shneka dlia transportuvannia misiachnoho reholitu. Zbirka tez ХХVІ Mizhnarodnoi molodizhnoi naukovo-praktychnoi konferentsii «Ludyna i kosmos», Dnipro, 17 – 19 kvitnia, 2024. S. 132 – 133.

12. Semenenko Ye. V. , Biliaiev M. M., Semenenko P. V. Rozrakhunok parametriv systemy transportuvannia misiachnogo reholitu. Space Technology. Missile Armaments. Zb.
nauk.-tekhn. st. 2024. Vyp. 1. Dnipro: DP «KB «Pivdenne». S. 93 – 101.
https://doi.org/10.33136/stma2024.01.093

13. Bezruchko K. A. Review of potential sources for obtaining energy carriers and mineral raw materials in outer space. Heotekhnichna mekhanika. 2022. № 163. S.140-154. https://doi.org/10.15407/geotm2022.163.140

14. Nouman Khan, Muhammad Kaleem Sarwar, Muhammad Rashid, Hafiz Kamran Jalil Abbasi, Saif Haider, Muhammad Atiq Ur Rehman Tariq, Abdullah Nadeem, Muhammad Ahmad
Zulfiqar, Ali Salem, Nadhir Al-Ansari, Abdelaziz M. Okasha, Ahmed Z. Dewidar&Mohamed A. Mattar. Development of a sustainable portable Archimedes screw turbine for hydropower generation. Scientific Reports. 2025. Vol. 15. Issue 1. DOI
https://doi.org/10.1038/s41598-025-90634-8

15. Kumar Thakur N., Thakur R., Kashyap K., Goel B. Efficiency enhancement in Archimedes screw turbine by varying different input parameters – An experimental study.
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]]> 2.1.2024 New and advanced liquid rocket engines of the Yuzhnoye SDO https://journal.yuzhnoye.com/content_2024_1-en/annot_2_1_2024-en/ Mon, 25 Aug 2025 07:00:07 +0000 https://journal.yuzhnoye.com/?page_id=34964
2024, (1); 9-18 DOI: https://doi.org/10.33136/stma2024.01.009 Language: Ukrainian Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Nowadays Yuzhnoye propulsion experts keep working on development of the advanced liquid rocket engines powered both by cryogenic and hypergolic propellants, which satisfy the majority of launch service market demands.
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2. New and advanced liquid rocket engines of the Yuzhnoye SDO

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Prokopchuk O. O., Shulga V. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 9-18

DOI: https://doi.org/10.33136/stma2024.01.009

Language: Ukrainian

Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Moreover, liquid engines design office was assigned with manufacturing and testing of the main rocket engines, developed by NPO Energomash and to be installed on Yuzhnoye-developed launch vehicles. Over the past 66 years Yuzhnoye SDO has developed more than 40 liquid rocket engines (LRE) of various purpose, designed both to gas-generator cycle and to staged combustion cycle. Seventeen of them were commercially produced by Yuzhmash PA and installed on launch vehicles. Nowadays Yuzhnoye propulsion experts keep working on development of the advanced liquid rocket engines powered both by cryogenic and hypergolic propellants, which satisfy the majority of launch service market demands. Within the framework of extensive cooperation with foreign space companies, on a contract basis, Yuzhnoye propulsion experts are working on the design and development testing of the liquid rocket engines, as well as their components. The accumulated vast experience in the development of liquid rocket engines nowadays enables high scientific and technical level in the creation of up-to-date engines, demanded in the world market. Significant steps in this area have been made by the experts from the Yuzhnoye propulsion division and then subsequent manufacture and delivery by Yuzhmash PA of the engine intended for the European rocket Vega Stage 4; and designing the individual components for the engines with thrusts ranging from 500 kgf to 200 tf ordered by foreign customers. This article provides the review of current and scheduled activities of the Yuzhnoye SDO to develop the liquid rocket engines within the thrust ranges from ~ 40 kgf to ~ 500 tf.

Key words: LOX-kerosene liquid rocket engines, hypergolic propellant liquid rocket engines, staged combustion cycle, main rocket engine, thrust, specific thrust impulse.

Bibliography:
  1. Zhidkostnye raketnye dvigateli, dvigatelnye ustanovki, bortovye istochniki moschnosti, razrabotannye KB dvigatelnykh ustanovok GP«KB «Yuzhnoye». Za nauk. red. akad. NAN Ukrainy S.M. Konyukhova, kand. tekhn. nauk V.M. Shnyakina. Dnipropetrovsk: DP «KB «Pivdenne», 2008. 466 ark.
  2. Prokopchyuk O. O., Shulga V. A., Khromyuk D. S., Sintyuk V. O. Zhidkostnye raketnye dvigateli GP«KB «Yuzhnoye»: nauk.-tekhn. zbirnyk. Za nauk. red. akademika NAN Ukrainy
    O. V. Degtyareva. Dnipro: ART-PRES, 2019. 440 ark.

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]]> 2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems https://journal.yuzhnoye.com/content_2020_1-en/annot_2_1_2020-en/ Thu, 20 Jun 2024 11:10:04 +0000 https://journal.yuzhnoye.com/?page_id=31001
The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.
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2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Aksenenko A. V.1, Hurskyi O. I.1, Klochkov A. S.1, Kondratiuk Ye. A.1, Senkin V. S.2, Siutkina-Doronina S. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2020, (1); 13-25

DOI: https://doi.org/10.33136/stma2020.01.013

Language: Russian

Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. The guided missiles of multiple launch rocket system are intended for delivering munitions to the given spatial point with required and specified kinematic motion parameters at the end of flight. The aim of the article is an analysis of the development trends of the guided missiles with the solid rocket motors for the multiple launch rocket systems, identifying the characteristics and requirements for the flight trajectories, design parameters, control programs, overall dimensions and mass characteristics, structural layout and aerodynamic schemes of missiles. The formalization of the complex task to optimize design parameters, trajectory parameters and motion control programs for the guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories is given. The complex task belongs to a problem of the optimal control theory with limitations in form of equa lity, inequality and differential constraints. To simplify the problem, an approach to program forming is proposed for motion control in the form of polynomial that brings the problem of the optimal control theory to a simpler problem of nonlinear mathematical programming. When trajectory parameters were calculated the missile was regarded as a material point of variable mass and the combined equations for center-of-mass motion of the guided missile with projections on axes of the terrestrial reference system were used. The structure of the mathematical model was given along with the calculation sequence of the criterion function that was used for determination of the optimal parameters, programs and characteristics. The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.

Key words: multiple launch rocket systems (MLRS), complex problem of the optimal control theory, problem of nonlinear mathematical programming, main solid rocket motor, limitations for motion parameters and basic characteristics of the guided missiles

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Effect of a guided rocket object’s lateral maneuver on the flight range and lateral deviation
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]]> 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. 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. Key words: Moon , regolith , auger , electric motor , capacity , power Bibliography: 1.
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11. Parameters calculation of the lunar regolith transport system

ISSN: 2617-5525

e-ISSN: 2617-5533

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:

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