Search Results for “Los' O. V.” – Collected book of scientific-technical articles

12.1.2024 Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge

manager — Mon, 17 Jun 2024 11:36:02 +0000

12. Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge

Authors:

Nadtoka V. M.¹, Shtapenko Ye. P.², Kraeva V. S.¹, Kraev M. V.¹

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; Ukrainian State University of Science and Technologies²

Page: Kosm. teh. Raket. vooruž. 2024, (1); 102-113

Language: Ukrainian

Annotation: Steel hardening technology is considered, which implies modification of the steel surface with the method of ion-plasma nitriding in glow discharge. Ion-plasma nitriding is a multi-factor process, which requires the study of the influence of nitriding process conditions on the structure of modified layers, which, in its turn, determines their mechanical properties. The subjects of research included: austenitic steel 12X18Н10T, carbon steel Ст3 and structural steel 45. There were two conditions of plasma creation during the research: free location of samples on the surface of the cathode (configuration I) and inside the hollow cathode (configuration II). Optimal parameters of the ion-plasma nitriding process have been determined, which provide stability of the process and create conditions for intensive diffusion of nitrogen into the steel surface. Hydrogen was added to the argon-nitrogen gaseous medium to intensify the nitriding process. Working pressure in the chamber was maintained within the range of 250-300 Pa, the duration of the process was 120 minutes. Comparative characteristics of the structure and microhardness of the modified surfaces of the steels under study for two ion-plasma nitriding technologies are presented. Metallographic examination of the structure of the surface modified layers in the cross section showed the presence of the laminated nitrided layer, which consists of different phases and has different depths, depending on the material of the sample and treatment mode. Nitrided layer of 12Х18Н10Т steel consisted of four sublayers: upper “white” nitride layer, double diffuse layer and lower transition layer. The total depth of the nitrided layer after the specified treatment time reached 23 μm, use of hollow cathode increased it by 26% to 29 μm. The nitrided layers of steel Ст3 and steel 45 consisted of two sublayers – thick “white” nitride layer and general diffuse layer with a thickness of about 18 μm. The microhardness of the nitrided layer of steel Ст3 was 480 HV, increasing by 2,5 times, and for steel 45 was 440 HV, increasing by 1,7 times. The use of hollow cathode for these steels reduces the depth of the nitrided layer, but at the same time the microhardness increases due to the formation of a thicker and denser nitride layer on the surface. The results of the conducted research can be used to strengthen the surfaces of the steel parts in rocket and space technology, applying high-strength coatings.

Key words: ion nitriding, glow discharge, cross-sectional layer structure, hardening, microhardness

Bibliography:

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2. Al-Rekaby D. W., Kostyk V., Glotka A., Chechel M. The choice of the optimal temperature and time parameters of gas nitriding of steel. Eastern-European journal of Enterprise Technologies. 2016. V. 3/5(81). P.44-49.
3. Yunusov A. I., Yesipov R. S. Vliyanie sostava gazovoy sredy na process ionnogo azotirovaniya martensitnoy stali 15Х16К5НР2МВФАБ-Ш. Vestnik nauki. 2023. №5(62). s. 854-863.
4. Zakalov O. V. Osnovy tertya i znoshuvannya u mashinah: navch. posibnik, vydavnytstvo TNTU im. I. Pulyuya, Ternopil. 2011. 332 s.
5. Kindrachuk M. V., Zagrebelniy V. V., Khizhnyak V. G., Kharchenko N. A. Technologichni aspeckty zabespechennya pratsezdatnosti instrument z shvydkorizalnykh staley. Problemy tertya ta znoshuvannya. 2016. №1 (70). S. 67-78.
6. Skiba M. Ye., Stechishyna N. M., Medvechku N. K., Stechishyn M. S., Lyukhovets’ V. V. Bezvodneve azotuvannya u tliyuchomu rozryadi, yak metod pidvyschennya znosostiykisti konstruktsiynykh staley. Visn. Khmelnitskogo natsionalnogo universitetu. 2019. №5. S. 7-12.
7. Axenov I. I. Vakkumno-dugovye pokrytiya. Technologiya, materialy, struktura i svoistva. Kharkov, 2015. 379 s.
8. Pastukh I. M., Sokolova G. N., Lukyanyuk N. V. Azotirovanie v tleyuschem razryade: sostoyanie i perspektyvy. Problemy trybologii. 2013. №3. S. 18-22.
9. Pastukh I. M. Teoriya i praktika bezvodorodnogo azotirovanniya v tleuschem razryade: izdatelstvo NNTs KhFTI. Kharkov, 2006. 364 s.
10. Sagalovich O. V., Popov V. V., Sagalovich V. V. Plasmove pretsenziyne azotuvannya AVINIT N detaley iz staley i splaviv. Technologicheskie systemy. 2019. №4. S. 50-56.
11. Kozlov A. A. Nitrogen potential during ion nitriding process in glow-discharge plasma. Science and Technique. 2015. Vol. 1. P. 79-90.
12. Nadtoka V., Kraiev M., Borisenko А., Kraieva V. Multi-component nitrated ion-plasma Ni-Cr coating. Journal of Physics and Electronics. 2021. №29(1). Р. 61–64. DOI 10.15421/332108.
13. Nadtoka V., Kraiev M., Borisenko A., Bondar D., Gusarova I. Heat-resistant MoSi2–NbSi2 and Cr–Ni coatings for rocket engine combustion chambers and respective vacuum-arc deposition technology/ 74th International Astronautical Congress (IAC-23-C2.4.2), Baku, Azerbaijan, 2-6 October 2023.
14. Kostik K. O., Kostik V. O. Porivnyalniy analiz vplyvu gazovogo ta ionno-plazmovogo azotuvannya na zminu struktury i vlastyvostey legovannoi stali 30Х3ВА. Visnik NTU «KhPI». 2014. №48(1090). S. 21-41.
15. Axenov I. I., Axenov D. S., Andreev A. A., Belous V. A., Sobol’ O.V. Vakuumno-dugovye pokrytiya: technologia, materialy, struktura, svoistva: VANT NNTs KhFTI, Kharkov. 2015. 380 s.
16. Pidkova V. Ya. Modyfikuvannya poverkhni stali 12Х18Н10Т ionnoyu implantatsieyu azotom. Technology audit and production reserves. 2012. Vol. 3/2(5). P. 51-52.
17. Kosarchuk V. V., Kulbovsliy I. I., Agarkov O. V. Suchasni metody zmitsnennya i pidvyschennya znosostiykosti par tertya. Ch. 2. Visn. Natsionalnogo transportnogo universytetu. 2016. Vyp. 1(34). S. 202-210.
18. Budilov V. V., Agzamov R. D., Ramzanov K. N. Issledovanie i razrabotka metodov khimiko-termicheskoy obrabotki na osnove strukturno-fasovogo modifitsirovaniya poverkhnisti detaley silnotochnymi razryadami v vakuume. Vestnik UGATU. Mashinostroenie. 2007. T. 9, №1(19). S. 140-149.
19. Abrorov A., Kuvoncheva M., Mukhammadov M. Ion-plasma nitriding of disc saws of the fiber-extracting machine. Modern Innovation, Systems and Technologies. 2021. Vol. 1(3). P. 30-35.
20. Smolyakova M. Yu., Vershinin D. S., Tregubov I. M. Issledovaniya vliyaniya nizkotemperaturnogo azotirovanniya na strukturno-fasoviy sostav i svoistva austenitnoy stali. Vzaimodeystvie izlecheniy s tverdym telom: materialy 9-oi Mezhdunarodnoy konferentsii (Minsk, 20-22 sentyabrya 2011 g.). Minsk, 2011. S. 80-82.
21. Adhajani H., Behrangi S. Plasma Nitriding of Steel: Topics in Mining, Metallurgy and Material Engineering by series editor Bergmann C.P. 2017. 186 p.
22. Fernandes B.B. Mechanical properties of nitrogen-rich surface layers on SS304 treated by plasma immersion ion implantation. Applied Surface Science. 2014. Vol. 310. P. 278-283.
23. Khusainov Yu. G., Ramazanov K. N., Yesipov R. S., Issyandavletova G. B. Vliyanie vodoroda na process ionnogo azotirovanniya austenitnoy stali 12Х18Н10Т. Vestnik UGATU. 2017. №2(76). S. 24-29.
24. Sobol’ O. V., Andreev A. A., Stolbovoy V. A., Knyazev S. A., Barmin A. Ye., Krivobok N. A. Issledovanie vliyaniya rezhimov ionnogo azotirovanniya na strukturu i tverdost’ stali. Vostochno-Yevropeyskiy journal peredovykh tekhnologiy. 2015. №2(80). S. 63-68.
25. Kaplun V. G. Osobennosti formirovanniya diffusionnogo sloya pri ionnom azotirovannii v bezvodorodnykh sredakh. FIP. 2003. T1, №2. S. 145.

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11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM

manager — Mon, 17 Jun 2024 08:41:21 +0000

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

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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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.
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.
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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.
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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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3.1.2024 Future projects of lunar exploration implemented by Yuzhnoye SDO

manager — Wed, 12 Jun 2024 15:28:59 +0000

3. Future projects of lunar exploration implemented by Yuzhnoye SDO

Authors:

Husarova I. O., Lysenko Yu. O., Osinovyi G. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 19-28

Language: English

Annotation: Over the past years, the leading space powers have been returning to the idea of expeditions to the Moon and actively designing and manufacturing components for inhabited lunar bases. Yuzhnoye State Design Office has its own concept of a lunar base and, of course, cannot stand aside from the solution of scientific and technical problems related to the Moon exploration. Specialists of Yuzhnoye SDO completed conceptual development of a significant range of technologies required for the Moon exploration: a space transportation system for lunar expeditions; landers to deliver payloads to the surface of the Moon and transport experimental equipment; mobile laboratories; a reconnaissance rover to provide reconnaissance missions on the surface of the Moon; vehicles to provide lifting and transport, assembly and construction, production and technological and soil extraction work on the surface of the Moon; habitat units and other elements of the lunar infrastructure. Taking into account the high costs of lunar exploration, it is clear that international cooperation is the most realistic scenario for Yuzhnoye SDO to participate in the exploration. The U.S. lunar program is the most attractive. Private companies that NASA selects for the lunar programs can become partners of Yuzhnoye. With a view to ensuring the participation of Yuzhnoye SDO in international programs, the current state of global technologies for the Moon exploration was analyzed and opportunities to promote technologies developed by Ukrainian specialists on the international market of space technologies were identified based on the analysis. Taking into account the high level of technologies developed by the potential partners, it is proposed for the first time to consider it advisable to promote Yuzhnoye’s technologies with TRL 6–9 which have already been successfully tested and the innovative technologies developed by the company which have no analogues in the world or surpass the world level in terms of their technological and economic performance. Based on the analysis of the Lunar Industrial & Research Base conceptual design, such technologies may include rocket propulsion, units and assemblies of liquid-propellant propulsion (TRL 6–9), as well as future designs such as a hydrogen energy accumulator and inert anodes made of ultra-high-temperature ceramics for electrolysis of regolith melts.

Key words: rocket propulsion, hydrogen energy accumulator, inert anodes.

Bibliography:

Rosiya vtratyla “Lunu-25”, India uspishno zavershyla misiu. Chomu krainy ponovyly gonku za resursy Misyatsa? 23 serpnya 2023. https://www.epravda.com.ua/publications/2023/08/23/703510 (Russia lost Luna-25, India successfully completed the mission. Why have countries renewed the race for lunar resources? August 23, 2023. In Ukrainian)
Creech S, Guidi J, Elburn D. Artemis: An overview of NASA’s activities to return humans to the Moon. Paper presented at: 2022 IEEE Aerospace Conference (AERO); 2022 Mar 05–12; Big Sky, Montana.

3 In-Situ Resource Utilization (ISRU) Demonstration Mission, 2019. https://exploration.esa.int/web/moon/-/60127-in-situ-resource-utilisation-demonstration-mission.

4 Peng Zhang, Wei Dai, Ran Niu, Guang Zhang, +12 authors. Overview of the Lunar In Situ Resource Utilization Techniques for Future Lunar Missions. Journal Space: Science & Technology. 2023, Vol. 3, Р. 1-18. Article ID: 0037. DOI: 10.34133/space.0037

Lin XU, Hui LI, Pei Z, Zou Y, Wang C. A brief introduction to the International Lunar Research Station Program and the Interstellar Express Mission. Chinese J Space Sci. 2022;42(4):511–513.
Li C, Wang C, Wei Y, Lin Y. China’s present and future lunar exploration program. Science. 2019;365(6450):238–239.
Ukrinform, 09 sichnya 2024, https://www.ukrinform.ua/rubric-technology/3804665-aponskij-zond-uvijsov-do-orbiti-misaca-pered-posadkou.html (Ukrinform, January 9, 2024. In Ukrainian).
Nimechina priednalasya do programmy vyvchennya Misyatsa Artemis, 15.09.2023, https://www.dw.com/uk/nimeccina-priednalas-do-programi-vivcenna-misaca-artemis/a-66826693 (Germany joined the Artemis moon exploration program, September 15, 2023. In Ukrainian).
Grigoriev O. N., Frolov G. A., Evdokimenko Yu. I., Kisel’ V. M., Panasyuk A. D., Melakh L. M., Kotenko V. A., Koroteev A. V. Ultravysokotemperaturnaya keramika dlya aviatsionno-kosmicheskoy techniki, Aviatsionno-kosmicheskaya technika i technologiya, 2012, No 8 (95), st.119-128 (O.N. Grigoriev, G.A. Frolov, Yu.I. Evdokimenko, V.M. Kisel, A.D. Panasyuk, L.M. Melakh, V.A. Kotenko, A.V. Koroteev. Ultra-high-temperature ceramics for aerospace engineering, Aerospace engineering and technology, 2012, No. 8 (95), Р. 119-128. In Russian).

10. Grigoriev O. N. et al. Oxidation of ZrB₂–SiC–ZrSi₂ ceramics in oxygen. Journal of the European Ceramic Society 30 (2010). 2397–2405.

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Виктория Лемех — Tue, 09 Jan 2024 13:29:00 +0000

Документи щодо організації освітньої діяльності

Документи щодо організації освітньої діяльності

• Концепція освітньої діяльності Державного підприємства “Конструкторське бюро “Південне” імені М.К. Янгеля”

• Положення про порядок здійснення освітньої діяльності на третьому етапі вищої освіти здобуття ступеня доктора філософії

• Договір про співробітництво між ДП “КБ “Південне” та Дніпровським національним університетом № 5-18 від 17.07.2018

• Положення про наукового керівника здобувача наукового ступеня доктора філософії в аспірантурі ДП “КБ “Південне” ім. М.К. Янгеля”

• Положення про підвищення кваліфікації (стажування) науково-педагогічних працівників

Освітньо-наукова програма

Освітньо-наукова програма “Авіаційна та ракетно-космічна техніка”

• ОНП

⇒ 2017
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ДП «Івченко-Прогрес»

Дніпровського національного університу

Інститут технічної механіки

Національного центру аерокосмічної освіти молоді

ПРО НАС

1. Ліцензія на підготовку докторів філософії

2. Гарант, група забезпечення ОНП, група забезпечення ОП

⇒ 2021
⇒ 2022

3. Сертифікати викладачів:
✓ Зєвако Василь Сергійович;
✓ Кирпита Тамара Володимирівна;
✓ Козак Леонід Романович;
✓ Логвиненко Анатолій Іванович;
✓ Потапович Лариса Петрівна;
✓ Трубін Анатолій Володимирович;
✓ Фролов Віктор Петрович;
✓ Хорошилов Віктор Сергійович.

4. Положення про аспірантуру

5. Колектив аспірантури

18.1.2020 Development of autonomous power engineering systems with hydrogen energy storage

Вацлав Самусевич — Wed, 13 Sep 2023 11:57:42 +0000

18. Development of autonomous power engineering systems with hydrogen energy storage

Authors:

Shevchenko A. A.¹, Kozak L. R.², Zipunnikov M. M.¹, Kotenko A. L.¹

Organization:

Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine¹; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine²

Page: Kosm. teh. Raket. vooruž. 2020, (1); 160-169

DOI: https://doi.org/10.33136/stma2020.01.160

Language: Russian

Annotation: The article analyzes the energy potential of alternative sources of Ukraine. The projects using hydrogen technologies aimed at attracting solar energy to the infrastructure of energy technological complexes, in particular water desalination systems and for refueling automobile vehicles located in areas with high solar radiation potential, are considered. During the operation of water desalination plants using a solar power station as an energy source, contingencies are very likely to arise due to either a power outage (due to cloudy weather) or an emergency failure of individual elements of the system. In this case, it is required to ensure its removal from service without loss of technological capabilities (operability). For this purpose, it is necessary to provide for the inclusion in the technological scheme of the energy technological complex of an additional element that ensures operation of the unit for a given time, determined by the regulations for its operation. As such an element, a buffer system based on a hydrogen energy storage device is proposed. The current level of hydrogen technologies that are implemented in electrochemical plants developed at the Institute of Mechanical Engineering named after A. N. Podgorny of the National Academy of Sciences of Ukraine allows producing and accumulating the hydrogen under high pressure, which eliminates the use of compressor technology.

Key words: alternative energy sources, hydrogen, solar energy, hydrogen generator

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6. Shevchenko A. A., Zipunnikov M. М., Kotenko А. L., Vorobiova I. O., Semykin V. M. Study of the Influence of Operating Conditions on High Pressure Electrolyzer Efficiency. Journal of Mechanical Engineering. 2019. Vol. 22, № 4. P. 53–60. https://doi.org/10.15407/pmach2019.04.053

7. Clarke R. E., Giddey S., Ciacchi F. T., Badwal S. P. S., Paul B., Andrews J. Direct coupling of an electrolyser to a solar PV system for generating hydrogen. International Journal of Hydrogen Energy. 2009. № 34(6). P. 2531–2542. https://doi.org/10.1016/j.ijhydene.2009.01.053

8. Kunusch C., Puleston P. F., Mayosky M. A., Riera J. Sliding mode strategy for PEM fuel cells stacks breathing control using a super-twisting algorithm. IEEE Transactions on Control Systems Technology. 2009. № 17(1). P. 167–174. https://doi.org/10.1109/TCST.2008.922504

9. Mazloomi K., Gomes C. Hydrogen as an energy carrier: Prospects and challenges. Renew. Sustain. Energy Rev. 2012. № 16. P. 3024–3033. https://doi.org/10.1016/j.rser.2012.02.028

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11. Prystrii dlia oderzhannia vodniu vysokoho tysku: pat. 103681 Ukraina: MPK6 S 25V 1/12 / V. V. Solovey, A. A. Shevchenko, A. L. Kotenko, O. О. Makarov (Ukrajina). № 2011 15332; zajavl. 26.12.2011; opubl. 10.07.2013, Biul. № 21. 4 s.

12. Shevchenko А. А. Ispolzovanie ELAELov v avtonomnykh energoustanovkakh, kharakterizuyushchikhsia neravnomernostju energopostupleniia. Aviatsionno-kosmicheskaia tekhnika i technologiia: sb. nauch. tr. 1999. Vyp. 13. S. 111–116.

13. Solovey V. V., Zhirov А. S., Shevchenko А. А. Vliianie rezhimnykh faktorov na effektivnost elektrolizera vysokogo davleniia. Sovershenstvovaniie turboustanovok metodami matematicheskogo i fizicheskogo modelirovaniia: sb. nauch. tr. 2003. S. 250–254.

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12.1.2020 Modification of technology as the main course in the military transport aircraft development

Вацлав Самусевич — Wed, 13 Sep 2023 10:54:55 +0000

12. Modification of technology as the main course in the military transport aircraft development

Authors:

Los’ O. V.

Organization:

Antоnov Company, Kyiv, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 114-120

DOI: https://doi.org/10.33136/stma2020.01.114

Language: Russian

Annotation: The process of creating modifications of aircraft in the transport category is a very relevant and widespread phenomenon in modern aircraft construction. A separate group of military transport aircraft has been distinguished in connection with the specific character of their mission: – the need to formulate the characteristics “cargo – range” for light, medium, operational tactical and strategic military transport aircraft, since it is precisely according to this characteristic that they are positioned by their purpose; –specific requirements are imposed on military transport aircraft cargo compartment not only with respect to its geometrical dimensions and usable volume, but also with respect to the possibility of simultaneous accommodation of military equipment and people, as well as the placement of a stretcher with t he wounded during their evacuation from the war zone; – the possibility of airborne landing of military equipment and paratroopers, which requires specific hatches and means of maintaining weight balance in flight; – the possibility of basing on poorly prepared sites with a runway length of less than 800 m in the short take-off and landing (STL) mode, especially for operational tactical military-technical vehicles, which significantly expands their use in combat zones; – the possibility of conversion into a civilian aircraft: for the delivery of goods to areas of the far north, when fighting fires, when evacuating victims from disaster zones, etc. The article shows that creation of modifications of expensive military transport aircraft is the main direction of their development. All leading aircraft manufacturing companies in the world use modification procedures as the way to most quickly meet constantly changing requirements for military transport aircraft. Along with the traditional methods of designing the modifications, the domestic school proposed a new methodology for determining the necessary parameters for “deep” modifications in wing geometry and propulsion system. The methodology is based on the use of three principles: – ensuring growth of carrying capacity and the required range of modifications of military transport aircraft of various purposes; – geometric re-arrangement of wing and system of carrying surfaces “wing + tail units” according to the criterion of minimum inductive resistance when lifting forces are equal to basic version; – coordination of modifications in wing with the required parameters of propulsion system as a condition for ensuring the required fuel efficiency.

Key words: military transport aircraft, hallmarks of military transport aircraft modifications, principles of designing military transport aircraft modifications

Bibliography:

1. Krivov G. А. Mirovaia aviatsiia na rubezhe ХХ – ХХI stoletii. Promyshlennost, rynki. Kiev, 2003. 295 s.

2. Andrienko Yu. G. Metod formirovaniia sovokupnosti tekhniko-ekonomicheskikh kharakteristik v protsedure vybora proektnykh reshenii pri razrabotke transportnykh samoletov. Otkrytye informatsionnye i kompiuternye tekhnologii: sb. nauch. tr. NAU im. N. Е. Zhukovskogo “KhAI”. Kharkiv, 2002. Vyp. 12. С. 125–138.

3. Sheinin V. М. Rol’ modifikatsii v razvitii aviatsionnoi tekhniki. 1983. 226 s.

4. Babenko Yu. V. Metodika stoimostnoi otsenki modifikatsii blizhnemagistralnykh passazhirskikh samoletov. Aviatsionno-kosmicheskaia tekhnika i tekhnologiia: sb. nauch. tr. NAU im. N. Е. Zhukovskogo “KhAI”. Kharkiv, 2015. Vyp. 7(126). S. 145–149.

5. Los’ А. V. Poniatie koeffitsienta elliptichnosti trapetsievidnogo kryla i metod ego otsenki. Aviatsionno-kosmicheskaia tekhnika i tekhnologiia: sb. nauch. tr. NAU im. N. Е. Zhukovskogo “KhAI”. Kharkiv, 2019. Vyp. 9. S. 9–15.

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8.1.2020 Determining the main parameters of transport aircraft modifications considering the fuel efficiency

Вацлав Самусевич — Wed, 13 Sep 2023 10:34:58 +0000

8. Determining the main parameters of transport aircraft modifications considering the fuel efficiency

Authors:

Los’ O. V.

Organization:

Antоnov Company, Kyiv, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 85-89

DOI: https://doi.org/10.33136/stma2020.01.085

Language: Russian

Annotation: The main parameters are understood as: carrying capacity mг, range L and fuel efficiency qт, which largely determine the competitiveness of aircraft of this type, including military transport aircraft. The reason for the creation of modifications of transport category aircraft is the requirement for a constant increase in their flight performance by increasing the carrying capacity and range. Among the main goals of implementing such decisions there is an indispensable increase in the fuel efficiency of modifications, since the cost of fuel reaches 80 % of the cost of an airplane hour during operation. There are a number of models that make it possible to assess the influence of the weight and aerodynamic parameters of the airframe of the aircraft and the fuel performance of the power plant (specific engine consumption) on the integral indicator of the fuel efficiency of the modification at cruising mode and the average hourly fuel consumption at the certification stage, when all parameters of the airframe and engine are fixed and consideration of options is not possible. A new model is proposed for the stage of designing modifications, in which deep modification changes are made in the geometry of wing and in the power plant with various variants of their correlation and coordination. The parameters of new model: specific fuel efficiency – specific route productivity, in order to form the relative carrying capacity and relative range of action for the required specific fuel efficiency. An analysis of such dependencies showed: – with an increase in relative range L , fuel costs per flight also increase; – the adequacy of changes in route performance is observed only at L < 0.5. At L > 0.5 productivity is constantly decreasing, while the specific indicator of fuel consumption per unit of work increases exponentially; – if in the analysis we take into account the specific value of transport efficiency, that is, the characteristic “load – range” ( mп.н  f L ), it becomes obvious that the most favorable (from the point of view of fuel efficiency) are relative ranges of 0,3 < L < 0,5. In this range L , not only acceptable fuel efficiency values are realized, but also the maximum value of the route performance, that is the main parameters for which modifications are developed.

Key words: productivity, carrying capacity, fuel efficiency, parameter formation

Bibliography:

1. Balabuev P. V. Osnovy obshchego proektirovaniia samoletov s gazoturbinnymi dvigateliami. Kharkiv, 2003. Ch. 2. 389 s.

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3. Korol’ V. N. Kontseptsiia sozdaniia mezhdunarodnogo konsortsiuma “Srednii transportnyi samolet”. Voprosy proektirovaniia i proizvodstva konstruktsii letalelnykh apparatov. Kharkiv, 2002. Vyp. 30(3). S. 6-27.

4. Global Market Forecast. Future Journeys 2013 – 2020 / AIRBUS S.A.S Blagnac Cedex: Art @ Caractere, 2013. 125 p. [electronic resource]. Access mode: http://www.airbus.com/company/market/forecast/elD=dam.

5. 747-400 Freighter Main deck cargo arrangements. Boeing, 2010 10 p. [electronic resource]. Access mode: http://www.boeing.com.

6. 6. ICAO. 3.2bn passengers used air transport in 2014. [electronic resource]. Access mode: http://www.aviatime.com/-en/airports/airports-news.

7. An-188. Srednii voenno-ttansportnyi samolet ukorochennogo vzleta i posadki. Kyiv, 2018. S. 118.

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5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

Вацлав Самусевич — Wed, 13 Sep 2023 06:15:53 +0000

5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

Authors:

Hudramovych V. S.², Sirenko V. M.¹, Klimenko D. V.¹, Hart Ye. L.³

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; The Institute of Technical Mechanics, Dnipro, Ukraine²; Oles Honchar Dnipro National University, Dnipro, Ukraine³

Page: Kosm. teh. Raket. vooruž. 2020, (1); 44-56

DOI: https://doi.org/10.33136/stma2020.01.044

Language: Russian

Annotation: The shell structures widely used in space rocket hardware feature, along with decided advantage in the form of optimal combination of mass and strength, inhomogeneities of different nature: structural (different thicknesses, availability of reinforcements, cuts-holes et al.) and technological (presence of defects arising in manufacturing process or during storage, transportation and unforseen thermomechanical effects). The above factors are concentrators of stress and strain state and can lead to early destruction of structural elements. Their different parts are deformed according to their program and are characterized by different levels of stress and strain state. Taking into consideration plasticity and creeping of material, to determine stress and strain state, the approach is effective where the calculation is divided into phases; in each phase the parameters are entered that characterize the deformations of plasticity and creeping: additional loads in the equations of equilibrium or in boundary conditions, additional deformations or variable parameters of elasticity (elasticity modulus and Poisson ratio). Then the schemes of successive approximations are constructed: in each phase, the problem of elasticity theory is solved with entering of the above parameters. The problems of determining the lifetime of space launch vehicles and launching facilities should be noted separately, as it is connected with damages that arise at alternating-sign thermomechanical loads of high intensity. The main approach in lifetime determination is one that is based on the theory of low-cycle and high-cycle fatigue. Plasticity and creeping of material are the fundamental factors in lifetime substantiation. The article deals with various aspects of solving the problem of strength and stability of space rocket objects with consideration for the impact of plasticity and creeping deformations.

Key words: shell structures, stress and strain state, structural and technological inhomogeneity, thermomechanical loads, low-cycle and high-cycle fatigue, lifetime

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23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

Вацлав Самусевич — Thu, 07 Sep 2023 12:35:25 +0000

23. On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

Authors:

Muliar Yu. M., Fedorov V. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 190-206

DOI: https://doi.org/10.33136/stma2018.02.190

Language: Russian

Annotation: Presented is the theoretical justification of the phenomenon of the inertia initiation under accelerated motion of the body, and gravity origin in the circumterrestrial space. There is no description of the physical nature of the inertia and gravity in the scientific publications. In the phenomenological approach under study, allowing for reflection properties of the space, earlier unknown interdependent information-physical link of the body and its mechanical particles with space under the accelerated motion was determined in the state of rest of the gravitation field as well as in the state of weightlessness. Alongside with the environment, eigenspace, i.e. configuration space of the body and corresponding metric lines of the space are considered. Idea of metric lines agrees with the concept of F. Wilczek, the American physicist, Nobel-Prize laureate, on the existence of the unobservable metric field in the real space. Solution of the problem rests on the example of the cantilever beam and mathematical model of the information reflection process, which for the first time takes into consideration previously unknown property of space reflection. Under the accelerated motion of the body reflection gains the acceleration vector dt d а     . In this case reflection manifests itself in the initiation of the beam of polarization vector under study   ~ in every point of the configuration space and is expressed as     ~ а . Value of the polarization vector equals the value of acceleration vector with negative sign. As a result metric lines of the configuration space under conditions of beam acceleration become polarized lines, generating vector information inertia field. Interaction of mechanical particles with the information inertia field in the configuration space generates physical inertia field of force, providing the real inertia under accelerated motion of the beam. (Relatively slow motion of bodies is studied as compared to the speed of light). According to the set forth unconventional approach the nature of the earth gravity is conditioned by the polarization of the radial metric lines of the circumterrestrial space. And polarization vector is directed to the center of the Earth and equals acceleration vector of the free fall with the same sign. Interaction of the body with specific mass with the vector information field of the Earth generates the physical force field of gravity. Article deals with the fundamental issues of theoretical physics and other fields of natural science. Materials of the conducted research are regarded as a potential scientific discovery.

Key words: configuration space, modified method of sections, information and vacuum environment, metric lines, property of space reflection, polarization, scalar information field, vector information field

Bibliography:

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12.1.2018 A Device for Soft Separation of Spacecraft from Launch Vehicle

Вацлав Самусевич — Tue, 05 Sep 2023 06:45:35 +0000

12. A Device for Soft Separation of Spacecraft from Launch Vehicle

Authors:

Bondar’ М. А., Voloshin V. V., Duplischeva О. М., Mikhailov K. F., Porubaimekh V. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 69-71

DOI: https://doi.org/10.33136/stma2018.01.069

Language: Russian

Annotation: The paper deals with the advantages and peculiarities of operation of a device for soft separation of spacecraft from launch vehicle.

Key words:

Bibliography:

1. Kolesnikov K. S., Kozlov V. I., Kokushkin V. V. Flying Vehicle Stages Separation Dynamics. М., 1977. 221 p.

2. Method of Satellite Separation from Launch Vehicle and Device to Implement the Method: Pat. 108515 Ukraine: MPK В64G1/64 (2006:01) / М. А. Bondar’, V. V. Voloshin, О. М. Duplishcheva, K. F. Mikhailov, V. I. Porubaimekh (Ukraine); applicant and patent holder is Yuzhnoye SDO. No. а201305544; appl. 29.04.13; publ. 12.05.16, Bull. No 9.

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