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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.
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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.
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16. Pidkova V. Ya. Modyfikuvannya poverkhni stali 12Х18Н10Т ionnoyu implantatsieyu azotom. Technology audit and production reserves. 2012. Vol. 3/2(5). P. 51-52.
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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.
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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.
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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)
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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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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

Bibliography:

1. Syvolapov V. Potentsial vidnovliuvanykh dzherel enerhii v Ukraini. Agroexpert. 2016. № 12 (101). S. 74–77.

2. Züttel A., Remhof A., Borgschulte A., Friedrichs O. Hydrogen: the future energy carrier. Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences. 2010. № 368(1923). Р. 3329–3342. https://doi.org/10.1098/rsta.2010.0113

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5. Schlapbach L. Technology: Hydrogen-fuelled vehicles. Nature. 2009. № 460(7257). P. 809. https://doi.org/10.1038/460809a

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

10. Sharma S., Ghoshal S. K. Hydrogen the future transportation fuel: From production to applications. Renew. Sustain. Energy Rev. 2015. № 43. P. 1151–1158. https://doi.org/10.1016/j.rser.2014.11.093

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.

14. Solovey V., Kozak L., Shevchenko A., Zipunnikov M., Campbell R., Seamon F. Hydrogen technology of energy storage making use of windpower potential. Problemy Mashinostroyeniya. Journal of Mechanical Engineering. 2017. Vol. 20, № 1. P. 62–68. https://doi.org/10.17721/fujcV6I2P73-79

15. Solovey V. V., Kotenko А. L., Vorobiova I. О., Shevchenko A. А., Zipunnikov M. М. Osnovnye printsipy raboty i algoritm upravleniya bezmembrannym elektrolizerom vysokogo davleniia. Problemy mashinostroyeniia. 2018. T. 21, №. 4. S. 57–63. https://doi.org/10.15407/pmach2018.04.057

16. Solovey V., Khiem N. T., Zipunnikov M. M., Shevchenko A. A. Improvement of the Membraneless Electrolysis Technology for Hydrogen and Oxygen Generation. French-Ukrainian Journal of Chemistry. 2018. Vol. 6, № 2. P. 73–79. https://doi.org/10.17721/fujcV6I2P73-79

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16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

Вацлав Самусевич — Wed, 13 Sep 2023 11:18:27 +0000

16. Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

Authors:

Furkalo S. A., Stelmakh K. L., Lazarev T. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 149-154

DOI: https://doi.org/10.33136/stma2020.01.149

Language: Russian

Annotation: Launch vehicle lift-off is one of the most critical phases of the whole mission requiring special technical solutions to ensure trouble-free and reliable launch. A source of increased risk is the intense thermal and pressure impact of rocket propulsion jet on launch complex elements and on rocket itself. The most accurate parameters of this impact can be obtained during bench tests, which are necessary to confirm the operability of the structure, as well as to clarify the parameters and configuration of the equipment and systems of complex. However, full-scale testing is expensive and significantly increases the development time of the complex. Therefore, a numerical simulation of processes is quite helpful in the design of launch complexes. The presented work contains simulation of liquid rocket engine combustion products jet flowing into the gas duct at the rocket lift-off, taking into account the following input data: the parameters of propulsion system, geometric parameters of launch complex elements, propulsion systems nozzles and gas duct. A three-dimensional geometric model of the launch complex, including rocket and gasduct, was constructed. The thermodynamic parameters of gas in the engine nozzle were verified using NASA CEA code and ANSYS Fluent. When simulating a multicomponent jet, the equations of conservation of mass, energy, and motion were solved taking into account chemical kinetics. The three-dimensional problem was solved in ANSYS Fluent in steady-state approach, using Pressure-based solver and RANS k-omega SST turbulence model. The calculation results are the gas-dynamic and thermodynamic parameters of jets, as well as distribution of gas-dynamic parameters at nozzle exit, in flow and in boundary layer at gas duct surface. The methodology applied in this work makes it possible to qualitatively evaluate the gas-dynamic effect of combustion products jets on gas duct for subsequent optimization of its design.

Key words: liquid rocket engine, combustion products, multicomponent flow, ANSYS Fluent

Bibliography:

1. Bonnie J. McBride, Sanford Gordon. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications. II. Users Manual and Program Descriptions: NASA Reference Publication 1311. 1996.

2. Ten-See Wang. Thermophysics Characterization of Kerosene Combustion. Journal of Thermophysics and Heat Transfer. 2001. № 2, Vol. 15. P. 140–147. https://doi.org/10.2514/2.6602

3. Maas U., Warnatz J. Ignition Processes in Carbon-Monoxide-Hydrogen-Oxygen Mixtures: Twenty-Second Symposium (International) on Combustion. The Combustion Institute, 1988. P. 1695–1704. https://doi.org/10.1016/S0082-0784(89)80182-1

4. Timoshenko V. I. Teoreticheskiie osnovy tekhnicheskoj gazovoj dinamiki. Kiev, 2013. S. 154–155.

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7.2.2017 Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants

Виктория Лемех — Tue, 08 Aug 2023 12:43:00 +0000

7. Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants

Authors:

Mikhalchishin R. V., Kuda S. А., Golovin D. Y., Brezgin М. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 35-40

Language: Russian

Annotation: The paper presents the results of comparative investigation into characteristics of methane, kerosene and hydrogen in pair with oxygen. The peculiarities of each of these components are shown. The optimal parameters are considered of pneumohydraulic supply system, including the designs of tanks, pressurization system and engine supply lines cooling system.

Key words:

Bibliography:

1. Tamura H., Ono F., Kumakawa A. LOX/Methane Staged Combustion Rocket Investigation. AIAA 87-1856.

2. Crocker A., Perry S. System, Sensitivity Studies of a LOX/Methane Expander Cycle Upper Stage Engine. AIAA 98-3674.

3. Kyoung-Ho Kim, Dae-Sung Ju. Development of “Chase-10” liquid rocket engine having 10tf thrust using LOX & LNG (Methane). AIAA-2006-4907. 2014.

4. Evaluation of Parameters of Liquid Oxygen Circulation in Cryogenic LRPS Colling System: Technical Note 22.8234.123 ST / Yuzhnoye SDO. 2014.

5. Belyayev N. M. Pneumohydraulic Systems. Calculation and Designing. М., 1988. 42 p.

6. Pavlyuk Y. S. Ballistic Designing of Rockets: Tutorial for universities. Chelyabinsk, 1996. 92 p.

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24.1.2019 Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware

manager — Wed, 24 May 2023 16:01:02 +0000

24. Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware

Authors:

Naiden O. O., Ivanov A. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 163-170

DOI: https://doi.org/10.33136/stma2019.01.163

Language: Russian

Annotation: Gasars is a new type of porous cast materials manufactured on the basis of metals and their alloys, some types of ceramics. The basis of the process is gas-eutectic conversion in the system metal-hydrogen. The process of investigation and creation of gasars was commenced in 1979 in the National Metallurgical Academy of Ukraine and is currently continued in Ukraine, the USA, China, Japan, South Korea, Poland and others. The gasars production technological process consists in melting the specified material (metal, alloy, ceramics) in hydrogen (or other active gas) atmosphere at a certain pressure. After the melt is saturated with active gas to a certain concentration, the crystallization process begins at which the pore formation process is launched. As the pores growth occurs perpendicular to crystallization front, the orientation of heat withdrawal influences pores location. So, for example, to obtain radial porosity, radial heat withdrawal is required. To obtain various structures, along with directed crystallization process, the pressure in crystallization chamber is an important factor, which drives the gasar morphology. The porous structure of gasars is diverse, there are the gasars with longitudinal, cylindrical, spherical, conical pores. It is possible to alternate the porosity layers and monolithic metal layers. The dimensions of gasars pores are in the limits from 10 μm to 10 mm at total porosity from 7 to 55 (75%). However, there is a possibility to obtain the pores with smaller diameter. The mechanical properties of gasars have a number of advantages as compared with conventional porous materials produced by different methods. Subsequent processing of the gasars does not differ from analogous non-porous materials, which is also an advantage over conventional porous materials. And in case when the diameter of pores is less than 50 μm, the exceedance of mechanical properties of gasars as compared with monolithic materials of the same chemical composition is observed. This is caused by the fact that the pores were formed during crystallization and at the action of pressure on a gasar, local hardening occurs. At present, the gasars have already found application as light and strong structural materials, filters, heat exchangers, dampers, slide bearings, catalyst elements, friction materials, etc. The use of gasars in space hardware will help to considerably reduce the mass of launch vehicle structural elements without worsening strength properties. The possibility of welding and soldering the gasars allows finding their application in the structure of propellant systems, compressed gas and propellants supply systems, creating filtering elements based on the gasars, including propellant spraying and mixing systems.

Key words: gasars, gas-eutectic conversion, eutectics, porosity

Bibliography:

1. Shapovalov V. I. Legirovanie vodorodom. D.: Zhurfond, 2013. 385 p.

2. Shapovalov V. TERMEC 2006 // International Conference on Processing and Manufacturing of Advanced Materials, July 4–8, 2006, Vancouver, Canada. Р. 529.

3. Komissarchuk Olga, Xu Zhengbin, Hao Hai, Zhang Xinglu, Karpov V. Pore structure and mechanical properties of directionally solidified porous aluminum alloys / Research & Development. Vol. 11, No.1, January 2014.

4. Karpov V. V., Karpov V. Yu. Vliyanie poristosti na teploprovodnost’ gazov/ Teoriya I praktica metallurgii. 2003. № 4.

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21.1.2016 Selection of Optimal Parameters of Wind Desalting System with Hydrogen Energy Storage Unit

Виктория Лемех — Tue, 23 May 2023 13:16:28 +0000

21. Selection of Optimal Parameters of Wind Desalting System with Hydrogen Energy Storage Unit

Authors:

Kalnysh R. V., Los’ S. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 128-132

Language: Russian

Annotation: The technique of selection of optimal parameters of a wind-desalinating complex with hydrogen energy storage system based on a wind speed annual prediction module is considered and the demonstration version of the wind-hydrogen complex is developed that allows to analyze operation of the complex and its separate units in real time.

Key words:

Bibliography:

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