Keywords cloud
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. 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.
]]>11. Parameters calculation of the lunar regolith transport system
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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2. Semenenko P. V. Sposoby transortirovki poleznykh iskopaemykh ot mesta ikh dobychi k mestu pererabotki v lunnykh usloviyukh. P. V. Semenenko, D. G. Groshelev, G. G. Osinoviy, Ye. V. Semenenko, N. V. Osadchaya. XVII conf. molodykh vchenykh «Geotechnichni problemy rozrobky rodovysch». m. Dnipro, 24 zhovtnya 2019 r. S. 7.
3. Berdnik A. I. Mnogorazoviy lunniy lander. A. I. Berdnyk, M. D. Kalyapin, Yu. A. Lysenko, T. K. Bugaenko. Raketno-kosmichny complexy. 2019. T. 25. №5:3-10. ISSN 1561-8889. https://doi.org/10.15407/knit2019.05.003
4. Semenenko Ye. V., Osadchaya N. V. Traditsionnye i netraditsionnye vydy energii, a takzhe kosmicheskie poleznye iskopaemye v okolozemnom prostranstve. Nauch.-parakt. conf. «Sovremennye raschetno-experimentalnye metody opredeleniya characteristic raketno-kosmicheskoy techniki». m. Dnipro, 10 – 12 grudnya 2019 r. S. 62 – 63.
5. Komatsu pobudue excavator dlya roboty na Misyatsi https://www.autocentre.ua/ua/ news/concept/komatsu-postroit-ekskavator-dlya-raboty-na-lune-1380272.html.
6. Help NASA Design a Robot to Dig on the Moon https://www.nasa.gov/directorates/ stmd/help-nasa-design-a-robot-to-dig-on-the-moon/
7. Robert E. Grimm. Geophysical constaints on the lunar Procellarum KREEP Terrane. Vol. 118, Issue 4. April 2013. P. 768-778. https://agupubs-onlinelibrary-wiley-com.translate. goog/doi/10.1029/2012JE004114?_x_tr_sl=en&_x_tr_tl=ru&_x_tr_hl=ru&_x_tr_pto=sc
https://doi.org/10.1029/2012JE004114
8. Chen Li. A novel strategy to extract lunar mare KREEP-rich metal resources using a silicon collector. Kuixian Wei, Yang Li, Wenhui Ma, Yun Lei, Han Yu, Jianzhong Liu. Journal of Rare Earths Vol. 41, Issue 9, September 2023, P. 1429-1436. https://www-sciencedirect-com.translate.goog/science/article/ abs/pii/S1002072122001910?_x_tr_sl=en&_x_tr_tl=ru&_x_tr_hl=ru&_x_tr_pto=sc https://doi. org/10.1016/j.jre.2022.07.002
9. Moon Village Association https://moon-villageassociation.org/about/
10. GLOBAL MOON VILLAGE. https://space-architect.org/portfolio-item/ global-moon-village//
11. Just G. H. Parametric review of existing regolith excavation techniques for lunar In Situ Resource Utilization (ISRU) and recommendations for future excavation experiments. G. H. Just, Smith K., Joy K. H., Roy M. J. https://doi.org/10.1016/j.pss.2019.104746
https://www.sciencedirect.com/science/article/pii/S003206331930162X
12. Anthony J. Analysis of Lunar Regolith Thermal Energy Storage. Anthony J. Colozza Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio NASA Contractor Report 189073. November 1991. S-9 https://denning.atmos.colostate.edu/readings/ lunar.regolith.heat.transfer.pdf
13. Obgruntuvannya vykorystannya shneka dlya utilizatsii vidkhodiv vuglezbagachennya z mozhlyvistyu pidvyschennya bezpeki energetychnoi systemy pidpriemstv. SLobodyannikova I. L., Podolyak K. K., Tepla T. D. Materialy XХІ Mizhnarod. conf. molodykh vchennykh (26 zhovt. 2023 roku, m. Dnipro). Dnipro: IGTM im. M.S. Polyakova NAN Ukrainy, 2023. S. 50–55.
14. Kulikivskiy V. L., Paliychuk V. K., Borovskiy V. M. Doslidzhennya travmuvannya zerna gvintovym konveerom. Konstryuvannya, vyrobnitstvo ta exspluatatsiya silskogospodarskykh mashin. 2016. Vyp. 46. S. 160 – 165. https://doi.org/10.3233/EPL-46204
14. Lyubin M. V., Tokarchuk O. A., Yaropud V. M. Osoblyvosti roboty krutopokhylennykh gvyntovykh transporterov pri peremischenni zernovoi produktsii. Tekhnika, energetika, transport APK. 216. № 3(95). S. 235 – 240.
15. Gevko R. B., Vitroviy A. O., Pik A. I. Pidvyschennya tekhnichnogo rivnya gnuchkykh gvyntovykh konveeriv. Ternopil: Aston, 2012. 204 s.
16. Bulgakov B. M., Adamchyuk V. V., Nadikto V. T., Trokhanyak O. M. Teoretichne obgruntuvannya parametriv gnuchkogo gvintovogo konveera dlya transportuvannya zernovykh materialiv. Visnyk agrarnoi nauki. 2023. № 4(841). S. 59 – 66.
17. New Views of the moon. Reviews in mineralogy and geochemistry. Eds. Joliff B.L., Wieczorek M.A., Shearer C.K., Neal C.R. Mineralogical Society of America. Reviews in mineralogy and geochemistry. 2006. Vol. 60. 721 p. DOI: 10.2138/rmg.2006.60.
18. Semenenko Ye. V. Nauchnye osnovy technologiy hydromechanizatsii otkrytoy razrabotki titan-cyrkonovykh rossypey. Yevgeniy Vladimirovich Semenenko. Kiev: Nauk. dumka, 2011. 232 s.
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Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 417 – Launch Safety, 2023 [Internet resource]. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 420 License to Operate a Launch Site.
]]>5. Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 40-50
DOI: https://doi.org/10.33136/stma2024.01.040
Language: English
Annotation: Despite stringent environmental requirements, modern launch vehicles/integrated launch vehicles (LV/ILV)
burn toxic propellants such as NTO and UDMH. Typically, such propellants are used in the LV/ILV upper
stages, where a small amount of propellant is contained; however, some LV/ILV still use such fuel in all
sustainer propulsion stages. For launch vehicles containing toxic rocket propellants, flight accidents may result
in the failed launch vehicle falling to the Earth’s surface, forming large zones of chemical damage to people
(the zones may exceed blast and fire zones). This is typical for accidents occurring in the first stage flight
segment, when an intact launch vehicle or its components (usually individual stages) with rocket propellants
will reach the Earth’s surface. An explosion and fire following such an impact will most likely lead to a massive
release of toxicant and contamination of the surface air. An accident during the flight segment of the LV/ILV
first stage with toxic rocket propellants, equipped with a flight termination system that implements emergency
engine shutdown in case of detection of an emergency situation, has been considered. To assess the risk
of toxic damage to a person located at a certain point, it is necessary to mathematically describe the zone
within which a potential impact of the failed LV/ILV will entail toxic damage to the person (the so-called zone
of dangerous impact of the failed LV/ILV). The complexity of this lies in the need to take into account the
characteristics of the atmosphere, primarily the wind. Using the zone of toxic damage to people during the fall
of the failed launch vehicle, which is proposed to be represented by a combination of two figures: a semicircle
and a half-ellipse, the corresponding zone of dangerous impact of the failed LV/ILV is constructed. Taking into
account the difficulties of writing the analytical expressions for these figures during the transition to the launch
coordinate system and further integration when identifying the risk, in practical calculations we propose to
approximate the zone of dangerous impact of the failed LV/ILV using a polygon. This allows using a known
procedure to identify risks. A generalization of the developed model for identifying the risk of toxic damage
to people involves taking into account various types of critical failures that can lead to the fall of the failed
LV/ILV, and blocking emergency engine shutdown during the initial flight phase. A zone dangerous for people
was constructed using the proposed model for the case of the failure of the Dnepr launch vehicle, where the
risks of toxic damage exceed the permissible level (10–6). The resulting danger zone significantly exceeds the
danger zone caused by the damaging effect of the blast wave. Directions for further improvement of the model
are shown, related to taking into account the real distribution of the toxicant in the atmosphere and a person’s
exposure to a certain toxic dose.
Key words: launch vehicle, critical failure, flight accident, zone of toxic damage to people, zone of dangerous impact of the failed launch vehicle, risk of toxic damage to people.
Bibliography:
- Hladkiy E. H. Protsedura otsenky poletnoy bezopasnosti raket-nositeley, ispolzuyuschaya geometricheskoe predstavlenie zony porazheniya obiekta v vide mnogougolnika. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2015. Vyp. 3. S. 50 – 56. [Hladkyi E. Procedure for evaluation of flight safety of launch vehicles, which uses geometric representation of object lesion zone in the form of a polygon. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2015. Issue 3. Р. 50 – 56. (in Russian)].
- Hladkiy E. H., Perlik V. I. Vybor interval vremeni blokirovki avariynogo vyklucheniya dvigatelya na nachalnom uchastke poleta pervoy stupeni. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-tech. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2011. Vyp. 2. s. 266 – 280. [Hladkyi E., Perlik V. Selection of time interval for blocking of emergency engine cut off in the initial flight leg of first stage. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2011. Issue 2. Р. 266 – 280. (in Russian)].
- Hladkiy E. H., Perlik V. I. Matematicheskie modeli otsenki riska dlya nazemnykh obiektov pri puskakh raket-nositeley. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2010. Vyp. 2. S. 3 – 19. [Hladkyi E., Perlik V. Mathematic models for evaluation of risk for ground objects during launches of launch-vehicles. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2010. Issue 2. P. 3 – 19. (in Russian)].
- NPAOP 0.00-1.66-13. Pravila bezpeki pid chas povodzhennya z vybukhovymy materialamy promyslovogo pryznachennya. Nabrav chynnosti 13.08.2013. 184 s [Safety rules for handling explosive substances for industrial purposes. Consummated 13.08.2013. 184 p.
(in Ukranian)]. - AFSCPMAN 91-710 RangeSafetyUserRequirements. Vol. 1. 2016 [Internet resource]. Link : http://static.e-publishing.af.mil/production/1/afspc/publicating/
afspcman91-710v1/afspcman91-710. V. 1. pdf. - 14 CFR. Chapter III. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 417 – Launch Safety, 2023 [Internet resource]. Link: http://law.cornell.edu/cfr/text/14/part-417.
- 14 CFR. Chapter III. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 420 License to Operate a Launch Site. 2022 [Internet resource]. Link: http://law.cornell.edu/cfr/text/14/part-420.
- ISO 14620-1:2018 Space systems – Safety requirements. Part 1: System safety.
- 9 GOST 12.1.005-88. Systema standartov bezopasnosti truda. Obschie sanitarno-gigienicheskie trebovaniya k vozdukhu rabochei zony. [GOST 12.1.005-88. Labor safety standards system. General sanitary and hygienic requirements to air of working zone].
- 10 Rukovodyaschiy material po likvidatsii avarijnykh bolshykh prolivov okislitelya АТ (АК) i goruchego NDMG. L.:GIPKh, 1981, 172 s. [Guidelines on elimination of large spillages of oxidizer NTO and fuel UDMH. L.:GIPH, 1981, 172 p. (in Russian)].
- 11 Kolichestvennaya otsenka riska chimicheskykh avariy. Kolodkin V. M., Murin A. V., Petrov A. K., Gorskiy V. G. Pod red. Kolodkina V. M. Izhevsk: Izdatelskiy dom «Udmurtskiy universitet», 2001. 228 s. [Quantitative risk assessment of accident at chemical plant. Kolodkin V., Murin A., Petrov A., Gorskiy V. Edited by Kolodkin V. Izhevsk: Udmurtsk’s University. Publish house, 2001. 228 p. (in Russian)].
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Keywords cloud
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.
]]>3. Future projects of lunar exploration implemented by Yuzhnoye SDO
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 19-28
DOI: https://doi.org/10.33136/stma2024.01.019
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:
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Keywords cloud
Hydrogen the future transportation fuel: From production to applications.
]]>18. Development of autonomous power engineering systems with hydrogen energy storage
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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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.
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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
17. Solovey V., Zipunnikov N., Shevchenko A., Vorobjova I., Kotenko A. Energy Effective Membrane-less Technology for High Pressure Hydrogen Electro-chemical Generation. French-Ukrainian Journal of Chemistry. 2018. Vol. 6, № 1. P.151–156. https://doi.org/10.17721/fujcV6I1P151-156
18. Solovey V. V., Zipunnikov М. М., Shevchenko А. А., Vorobiova І. О., Semykin V. M. Bezmembrannyi henerator vodniu vysokoho tysku. Fundamentalni aspekty vidnovliuvano-vodnevoi enerhetyky i palyvno-komirchanykh technologij / za zahal. red. Yu. М. Solonina. Kyiv, 2018. S. 99–107.
19. Matsevytyi Yu. M., Chorna N. A., Shevchenko A. A. Development of a Perspective Metal Hydride Energy Accumulation System Based on Fuel Cells for Wind Energetics. Journal of Mechanical Engineering. 2019. Vol. 22, № 4. P. 48–52. https://doi.org/10.15407/pmach2019.04.048
20. Phillips R., Edwards A., Rome B., Jones D. R., Dunnill C. W. Minimising the ohmic resistance of an alkaline electrolysis cell through effective cell design. Int. J. Hydrogen Energy. 2017. № 42. P. 23986–23994. https://doi.org/10.1016/j.ijhydene.2017.07.184
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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).
]]>5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep
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
Bibliography:
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Keywords cloud
Storage and Transportation of Chemical Products.
]]>9. On the Peculiarities of High-Temperature Rocket Propellants Drain from Delivery Means to Filling Tank for Closed Drain
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2018 (1); 53-57
DOI: https://doi.org/10.33136/stma2018.01.053
Language: Russian
Annotation: The paper presents the variation of parameters of gas-vapor mixture of hypergolic rocket propellant components in a filling tank in the process of rocket propellant components filling into it with “closed drainage” depending on tank filing coefficient and initial parameters of environment in the tank.
Key words:
Bibliography:
1. Cosmodrome / Under the general editorship of A. P. Vol’sky. М., 1977.
2. Berezhkovsky M. I. Storage and Transportation of Chemical Products. М., 1973.
3. Selection and Justification of Technology of Rocket Propellants Drain from Tank-Containers into OFS, FFS Tanks: Technical Note Cyclone-4 22.6840.155 СТ. Yuzhnoye SDO, 2005.
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2017 (1); 23-29 Language: Russian Annotation: The thermal analysis was made for external surfaces of a reusable high-altitude supersonic flying vehicle being a part of a space transportation system.
]]>4. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2017 (1); 23-29
Language: Russian
Annotation: The thermal analysis was made for external surfaces of a reusable high-altitude supersonic flying vehicle being a part of a space transportation system. The basic criteria were determined for selection of its heat-resistant and heat-protective structures.
Key words:
Bibliography:
1. Kondratenko F. I. et al. Aerodynamic Heating and Thermal Protection of Intercontinental Ballistic Missiles / F. I. Kondratenko, P. S. Savoysky, V. I. Sidov, I. M. Fomishenko. М, 1973. 288 p.
2 Avduyevsky V. S. et al. Fundamentals of Heat Transfer in Aerospace Engineering / V. S. Avduyevsky, B. M. Galitseisky, G. A. Glebov. М., 1975. 624 p.
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During transportation tank container is subjected to various kinds of mechanical actions (vibration, rolling and pitching in the sea, braking, transshipment), therefore intensive mixing of propellants occur. Article includes the measuring results of the gas liquid medium parameters inside the tank containers with fuel in the process of fuel transportation to Ukraine from PRC factories and estimations of the measuring results using the developed model which confirmed the quantitative nature of the mass exchange processes, included in the model, going on in the gas liquid medium during transportation of the tank container with fuel equipment. Key words: oxidizer , fuel , saturation by helium , tank container , transportation Bibliography: 1. oxidizer , fuel , saturation by helium , tank container , transportation .
]]>6. Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 38-44
DOI: https://doi.org/10.33136/stma2019.01.038
Language: Russian
Annotation: This article considers the issue of achievement of the specified value of propellants saturation by helium after their delivery from the manufacturers to the launch site. Knowing the fact that propellants gas saturation or gas separation processes are labour-consuming and costly this issue is of immediate interest. In order to solve this problem number of factors have been considered, which determine the value of gas saturation in the propellants delivered to the launch site and procedure to control the value of gas saturation by the fuel manufacturer has been developed. This procedure implies that shipping tank container is pressurized after being fueled with propellants at the manufacturer’s, the pressure is characterized by the value of the known initial deficit or excess of gas in the propellants, following which tank container is delivered to the launch site. During transportation tank container is subjected to various kinds of mechanical actions (vibration, rolling and pitching in the sea, braking, transshipment), therefore intensive mixing of propellants occur. As propellants mix, process of propellant saturation occurs when certain amount of gas transits from tank container’s gas volume into the liquid, therefore certain gas saturation is reached. Article includes the measuring results of the gas liquid medium parameters inside the tank containers with fuel in the process of fuel transportation to Ukraine from PRC factories and estimations of the measuring results using the developed model which confirmed the quantitative nature of the mass exchange processes, included in the model, going on in the gas liquid medium during transportation of the tank container with fuel equipment. It has been determined that due to inevitable errors in the measuring of the specified parameters by the tank container, the achievement of the specified gas saturation with high precision is problematic. In spite of the fact that this procedure does not provide exact value of the specified gas saturation, its application will accelerate and make cheaper the process of fuel preparation for filling operations at the launch site, which is especially relevant in case of fuel saturation by helium. Based on this fuel saturation by helium procedure, the complex technology is suggested, providing controlled gas saturation during fuel delivery and subsequent adjustment of gas saturation using launch site equipment. Therefore, this article develops and studies the original model of the controlled gas saturation of the fuel during its delivery to the consumer. Alternative of the practical use of the study results is suggested in the form of the complex technology of fuel saturation by helium, delivered in the tank containers from the manufacturer to the launch site.
Key words: oxidizer, fuel, saturation by helium, tank container, transportation
Bibliography:
1. Volskiy A. P. Kosmodrom. M.: Voenizdat, 1977. 311 p.
2. Stepanov A. N., Vorobiev A. M., Grankin B. K. Kompleksy zapravki raket I kosmicheskikh apparatov. SPB:OM-PRESS, 2004. 26 p.
3. Kiriyanova A. N., Matveeva O. P. Opredelenie kolebania davlenia v gazovoy polosti hermetychikh emkostey transportnozapravochnykh containerov dlya raketnykh topliv pri temperaturnykh vozdeistviyakh/ Nauka i innovatsii. 2016. Vyp. 7.
4. Berezhkovskiy M. I. Khranenie i transportirovka khimicheskykh produktov. – M.: Khimia, 1973. – 272 s.
5. Perepelkin K. Ye., Matveev V. S. Gazovye emulsii. L.:Khimia, 1979. 200 p.
6. Issledovanie protsessov degazirovaniya komponentov topliva v conteinere-tsisterne pri dostavke topliva potrebitelyu. Cyclone4M 21.18425.174 OT: Techn. report. Dnepropetrovsk: Yuzhnoye SDO, 2017. 39 p.
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Keywords cloud
14 CFR, Commercial space transportation, Federal aviation administration, Department of transportation Subchapter C – Licensing, part 420 – License to Operate a Launch Site, 2000 20.
]]>2. How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2023 (1); 14-30
DOI: https://doi.org/10.33136/stma2023.01.014
Language: Ukrainian
Annotation: Safety of the up-to-date rocket and space complexes remains a topical problem for the developers of rocket and space technology. The integral component of this problem along with the safety of operations during launch vehicle ground pre-launch processing is organization of flight safety. The basic task of this rocket and space complexes safety component is to prevent or minimize serious consequences in case of launch vehicle failure in the flight leg, after all such accidents can cause damage to the population and facilities (including personnel and facilities of the ground complex), located along the flight paths. It is shown that the flight safety assurance of the launch vehicle is based on the experience of combat missile systems. Flight safety during the launch vehicle launches is provided by laying flight paths through sparsely populated (unpopulated) territories and using special onboard flight safety systems. This system limits the size of impact zones of emergency launch vehicle and its debris by emergency engine shutdown. Recently flight safety process is organized based on the acceptable risk concept. It is based on a risk assessment for the ground-based facilities and people, and it should not exceed the established standards. Such approach requires development and upgrading of the mathematical models of risk assessment in case of launch vehicle failure in the flight phase. Formation of the risk-oriented approach to flight safety in Yuzhnoye SDO is shown. Key moment in this process is to develop the separate structural unit, which started working on rocket and space complexes flight safety assurance and analysis. The basic model for assessing the risks of damage to facilities and people is analyzed, using the maximum impact zone of an emergency launch vehicle, which is realized in case of loss of control and flight safety system activation. The main directions of the basic model improvement are shown, which led to the development of a number of new original models of flight safety assessment in the Yuzhnoye SDO. First of all, the developed models take into account the flight safety system specifics, which are used to equip the launch vehicles, developed by Yuzhnoye SDO: criteria of activation, blocking of the engine emergency shutdown in the initial flight phase and Fe functional. Such models allow to take into account the different nature of emergency situations in the launch vehicle flight phase and ways of their representation, representation of the damage areas of facilities in the form of convex polygons, possible fragmentation of the emergency launch vehicle at the free- fall leg etc. The developed models have found wide application in the practice of assessing flight safety indicators in the Yuzhnoye SDO projects.
Key words: launch vehicle, acceptable risk, launch vehicle failure in the flight phase, flight safety system, emergency launch vehicle impact zone, risk of damage to facilities, collection risk
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