Keywords cloud
The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.
]]>2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2020, (1); 13-25
DOI: https://doi.org/10.33136/stma2020.01.013
Language: Russian
Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. The guided missiles of multiple launch rocket system are intended for delivering munitions to the given spatial point with required and specified kinematic motion parameters at the end of flight. The aim of the article is an analysis of the development trends of the guided missiles with the solid rocket motors for the multiple launch rocket systems, identifying the characteristics and requirements for the flight trajectories, design parameters, control programs, overall dimensions and mass characteristics, structural layout and aerodynamic schemes of missiles. The formalization of the complex task to optimize design parameters, trajectory parameters and motion control programs for the guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories is given. The complex task belongs to a problem of the optimal control theory with limitations in form of equa lity, inequality and differential constraints. To simplify the problem, an approach to program forming is proposed for motion control in the form of polynomial that brings the problem of the optimal control theory to a simpler problem of nonlinear mathematical programming. When trajectory parameters were calculated the missile was regarded as a material point of variable mass and the combined equations for center-of-mass motion of the guided missile with projections on axes of the terrestrial reference system were used. The structure of the mathematical model was given along with the calculation sequence of the criterion function that was used for determination of the optimal parameters, programs and characteristics. The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.
Key words: multiple launch rocket systems (MLRS), complex problem of the optimal control theory, problem of nonlinear mathematical programming, main solid rocket motor, limitations for motion parameters and basic characteristics of the guided missiles
Bibliography:
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9. Gurov S. V. Reaktivnye sistemy zalpovogo ognia: obzor. 1-е izd. Tula, 2006. 432 s.
10. The new M30A1 GMLRS Alternate Warhead to replace cluster bombs for US Army Central 71601171. URL: https://www.armyrecognition.com/weapons_defence_industry_military_technology_uk/the_new_m30a1_gmlrs_alternate_warhead_to_replace_cluster_bombs_for_us_army_central_71601171.html (Access date 01.09.2019).
11. High-Mobility Artillery Rocket System (HIMARS), a member of MLRS family. URL: https://army-technology.com/projects/himars/ (Access date 01.09.2019).
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15. Krotov V. F., Gurman V. I. Metody I zadachi optimalnogo upravleniia. М., 1973. 446 s.
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20. Burov М. А., Varfolomeev V. I., Volkov L. I. Proektirovanie i ispytanie ballisticheskikh raket / pod red. V. I. Varfolomeeva, М. I. Kopytova. М., 1970. 392 s.
21. Siutkina-Doronina S. V. K voprosu optimizatsii proektnykh parametrov i programm upravleniia raketnogo ob’ekta s raketnym dvigatelem na tverdom toplive. Aviatsionno-kosmicheskaia tekhnika i tekhnologiia. 2017. № 2 (137). S. 44–59.
22. Aksenenko A. V., Baranov E. Yu., Hursky A. I., Klochkov A. S., Morozov A. S., Alpatov A. P., Senkin V. S., Siutkina-Doronina S. V. Metodicheskoe obespechenie dlia optimizatsii na nachalnom etape proektirovaniia proektnykh parametrov, parametrov traektorii i programm upravleniia dvizheniem raketnogo ob’ekta. Kosmicheskaia tekhnika. Raketnoe vooruzhenie: sb. nauch.-tekhn. st. / GP “KB “Yuzhnoye”. Dnipro, 2018. Vyp. 2 (116). S. 101–116. https://doi.org/10.33136/stma2018.02.101
23. Metodicheskoe obespechenie dlia optimizatsii na nachalnom etape proektirovaniia proektnykh parametrov, programm upravleniia, ballisticheskikh, energeticheskikh i gabaritno-massovykh kharakteristik upravliaemykh raketnykh ob’ektov, osushchestvliaiushchikh dvizhenie po aeroballisticheskoi traektorii: otchet po NIR / ITM NANU i GKAU, GP “KB “Yuzhnoye”. Dnepropetrovsk, 2017. 159 S.
24. Senkin V. S. K Vyboru programm upravleniia dvizheniem raketnogo ob’ekta po ballisticheskoi traektorii. Tekhnicheskaia mekhanika. 2018. № 1. S. 48–59.
25. Alpatov A. P., Senkin V. S. Metodicheskoe obespechenie dlia vybora oblika, optimizatsii proektnykh parametrov i programm upravleniia poletom rakety-nositelia. Tekhnicheskaia mekhanika. 2013. № 4. S. 146–161.
26. Alpatov A. P., Senkin V. S. Kompleksnaia zadacha optimizatsii osnovnykh proektnykh parametrov i programm upravleniia dvizheniem raket kosmicheskogo naznacheniia. Tekhnicheskaia mekhanika. 2011. № 4. S. 98–113.
27. Senkin V. S. Optimizatsiia proektnykh parametrov rakety-nositelia sverkhlegkogo klassa. Tekhnicheskaia mekhanika. 2009. № 1. S. 80–88.
28. Lebedev А. А., Gerasiuta N. F. Ballistika raket. М., 1970. 244 s.
29. Razumev V. F., Kovalev B. K. Osnovy proektirovaniia ballisticheskikh raket na tverdom toplive: ucheb. posobie dlia vuzov. М., 1976. 356 s.
30. Erokhin B. Т. Teoreticheskie osnovy oroektirovaniia RDTT. М., 1982. 206 s.
31. Abugov D. I., Bobylev V. М. Teoriia i raschet raketnykh dvigatelei tverdogo topliva: uchebnik dlia mashinostroitelnykh vuzov. М., 1987. 272 s.
32. Shishkov А. А. Gasodinamika porokhovykh raketnykh dvigatelei: inzhenernye metody rascheta. М., 1974. 156 s.
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2024, (1); 93-101 DOI: https://doi.org/10.33136/stma2024.01.093 Language: Ukrainian Annotation: The objective of this article is to develop a scientifically proven method of calculation of the auger conveyor parameters, such as the conveyor capacity and the corresponding power of the electrical motor, for different densities and porosities of conveyed materials, the geometrical parameters of the auger, and the specificity of the gravitational fields at the place of transportation. It gave the possibility, for the first time for the lunar environment, to suggest a procedure to calculate the auger conveyor parameters, such as the conveyor capacity and the corresponding power of the electric motor, using known geometrical parameters of the mainline and pipeline, the auger conveyor filling ratio and the parameters of the selected electrical motor. Key words: Moon , regolith , auger , electric motor , capacity , power Bibliography: 1.
]]>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:
1. Pustovgarov A. A., Osinoviy G. G. Kontseptsiya shlyuzovogo modulya misyachnoi bazy. ХХV Mizhnarodna molodizhna naukovo-praktychna conf. «Lyudyna i cosmos». Zbirnyk tez, NTsAOM, Dnipro, 2023. S. 86 – 87.
2. Semenenko P. V. Sposoby transortirovki poleznykh iskopaemykh ot mesta ikh dobychi k mestu pererabotki v lunnykh usloviyukh. P. V. Semenenko, D. G. Groshelev, G. G. Osinoviy, Ye. V. Semenenko, N. V. Osadchaya. XVII conf. molodykh vchenykh «Geotechnichni problemy rozrobky rodovysch». m. Dnipro, 24 zhovtnya 2019 r. S. 7.
3. Berdnik A. I. Mnogorazoviy lunniy lander. A. I. Berdnyk, M. D. Kalyapin, Yu. A. Lysenko, T. K. Bugaenko. Raketno-kosmichny complexy. 2019. T. 25. №5:3-10. ISSN 1561-8889. https://doi.org/10.15407/knit2019.05.003
4. Semenenko Ye. V., Osadchaya N. V. Traditsionnye i netraditsionnye vydy energii, a takzhe kosmicheskie poleznye iskopaemye v okolozemnom prostranstve. Nauch.-parakt. conf. «Sovremennye raschetno-experimentalnye metody opredeleniya characteristic raketno-kosmicheskoy techniki». m. Dnipro, 10 – 12 grudnya 2019 r. S. 62 – 63.
5. Komatsu pobudue excavator dlya roboty na Misyatsi https://www.autocentre.ua/ua/ news/concept/komatsu-postroit-ekskavator-dlya-raboty-na-lune-1380272.html.
6. Help NASA Design a Robot to Dig on the Moon https://www.nasa.gov/directorates/ stmd/help-nasa-design-a-robot-to-dig-on-the-moon/
7. Robert E. Grimm. Geophysical constaints on the lunar Procellarum KREEP Terrane. Vol. 118, Issue 4. April 2013. P. 768-778. https://agupubs-onlinelibrary-wiley-com.translate. goog/doi/10.1029/2012JE004114?_x_tr_sl=en&_x_tr_tl=ru&_x_tr_hl=ru&_x_tr_pto=sc
https://doi.org/10.1029/2012JE004114
8. Chen Li. A novel strategy to extract lunar mare KREEP-rich metal resources using a silicon collector. Kuixian Wei, Yang Li, Wenhui Ma, Yun Lei, Han Yu, Jianzhong Liu. Journal of Rare Earths Vol. 41, Issue 9, September 2023, P. 1429-1436. https://www-sciencedirect-com.translate.goog/science/article/ abs/pii/S1002072122001910?_x_tr_sl=en&_x_tr_tl=ru&_x_tr_hl=ru&_x_tr_pto=sc https://doi. org/10.1016/j.jre.2022.07.002
9. Moon Village Association https://moon-villageassociation.org/about/
10. GLOBAL MOON VILLAGE. https://space-architect.org/portfolio-item/ global-moon-village//
11. Just G. H. Parametric review of existing regolith excavation techniques for lunar In Situ Resource Utilization (ISRU) and recommendations for future excavation experiments. G. H. Just, Smith K., Joy K. H., Roy M. J. https://doi.org/10.1016/j.pss.2019.104746
https://www.sciencedirect.com/science/article/pii/S003206331930162X
12. Anthony J. Analysis of Lunar Regolith Thermal Energy Storage. Anthony J. Colozza Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio NASA Contractor Report 189073. November 1991. S-9 https://denning.atmos.colostate.edu/readings/ lunar.regolith.heat.transfer.pdf
13. Obgruntuvannya vykorystannya shneka dlya utilizatsii vidkhodiv vuglezbagachennya z mozhlyvistyu pidvyschennya bezpeki energetychnoi systemy pidpriemstv. SLobodyannikova I. L., Podolyak K. K., Tepla T. D. Materialy XХІ Mizhnarod. conf. molodykh vchennykh (26 zhovt. 2023 roku, m. Dnipro). Dnipro: IGTM im. M.S. Polyakova NAN Ukrainy, 2023. S. 50–55.
14. Kulikivskiy V. L., Paliychuk V. K., Borovskiy V. M. Doslidzhennya travmuvannya zerna gvintovym konveerom. Konstryuvannya, vyrobnitstvo ta exspluatatsiya silskogospodarskykh mashin. 2016. Vyp. 46. S. 160 – 165. https://doi.org/10.3233/EPL-46204
14. Lyubin M. V., Tokarchuk O. A., Yaropud V. M. Osoblyvosti roboty krutopokhylennykh gvyntovykh transporterov pri peremischenni zernovoi produktsii. Tekhnika, energetika, transport APK. 216. № 3(95). S. 235 – 240.
15. Gevko R. B., Vitroviy A. O., Pik A. I. Pidvyschennya tekhnichnogo rivnya gnuchkykh gvyntovykh konveeriv. Ternopil: Aston, 2012. 204 s.
16. Bulgakov B. M., Adamchyuk V. V., Nadikto V. T., Trokhanyak O. M. Teoretichne obgruntuvannya parametriv gnuchkogo gvintovogo konveera dlya transportuvannya zernovykh materialiv. Visnyk agrarnoi nauki. 2023. № 4(841). S. 59 – 66.
17. New Views of the moon. Reviews in mineralogy and geochemistry. Eds. Joliff B.L., Wieczorek M.A., Shearer C.K., Neal C.R. Mineralogical Society of America. Reviews in mineralogy and geochemistry. 2006. Vol. 60. 721 p. DOI: 10.2138/rmg.2006.60.
18. Semenenko Ye. V. Nauchnye osnovy technologiy hydromechanizatsii otkrytoy razrabotki titan-cyrkonovykh rossypey. Yevgeniy Vladimirovich Semenenko. Kiev: Nauk. dumka, 2011. 232 s.
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Keywords cloud
2024, (1); 29-39 DOI: https://doi.org/10.33136/stma2024.01.029 Language: Ukrainian Annotation: The article gives the analysis results for the servo drives dynamics, obtained from the theoretical calculations and during the development testing of the high power electric drives.
]]>4. The dynamics of servo drives
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 29-39
DOI: https://doi.org/10.33136/stma2024.01.029
Language: Ukrainian
Annotation: The article gives the analysis results for the servo drives dynamics, obtained from the theoretical calculations
and during the development testing of the high power electric drives. Theoretical research was conducted,
using the complete mathematical model of the servo drive, which included the equations of the control
signal shaping path, electric motor, reducer and load. The equations of the control signal shaping network
include only the characteristics of the compensating element in the assumption that all other delays in the
transformation path are minimized. The electric motor equations are assumed in the classical form, taking into
account the influence of the following main parameters on the motor dynamics: inductance and stator winding
resistance, torque and armature reaction coefficients and rotor moment of inertia. Interaction of the motor with
the multimass system of the reducer and load is presented in the form of force interaction of two masses –
a reduced mass of the rotor and mass of the load through the certain equivalent rigidity of the kinematic chain.
To describe the effect of gap in the kinematic connection the special computational trick, which considerably
simplifies its mathematical description, is used. Efficiency of the reducer is presented in the form of the internal
friction, proportional to the transmitted force. Calculation results with the application of the given mathematical
model match well with the results of the full-scale testing of different specimens of servo drives, which makes
it possible to use it for the development of new servomechanisms, as well as for the correct flight simulation
when testing the aircraft control systems. In particular, based on the frequency response calculations of the
closed circuit with the application of the given mathematical model, it is possible to define optimal parameters
of the correcting circuit. Reaction on the step action with the various values of circular amplification coefficient
in the circuit gives complete information on the stability regions of the closed circuit and influence of various
drive parameters on these regions. Based on the conducted theoretical and experimental studies, the basic
conclusions and recommendations were obtained and presented, accounting and implementation of which will
provide high dynamic characteristics of the newly designed servo drives.
Key words: electric drive, servo drive, reducer, stability, mathematical model.
Bibliography:
- Kozak L. Dynamika servomechanismov raketnoy techniki. Inzhenernye metody issledovaniya. Izd-vo LAP LAMBERT Academic Publiching, Germania. 2022.
- Kozak L. R., Shakhov M. I. Matematicheskie modely hydravlicheskikh servomekhanismov raketno-kosmicheskoy techniki. Kosmicheskaya technika. Raketnoe vooruzhenie. 2019. Vyp. 1.
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Keywords cloud
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.
]]>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
2024, (1); 9-18 DOI: https://doi.org/10.33136/stma2024.01.009 Language: Ukrainian Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Nowadays Yuzhnoye propulsion experts keep working on development of the advanced liquid rocket engines powered both by cryogenic and hypergolic propellants, which satisfy the majority of launch service market demands.
]]>2. New and advanced liquid rocket engines of the Yuzhnoye SDO
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 9-18
DOI: https://doi.org/10.33136/stma2024.01.009
Language: Ukrainian
Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Moreover, liquid engines design office was assigned with manufacturing and testing of the main rocket engines, developed by NPO Energomash and to be installed on Yuzhnoye-developed launch vehicles. Over the past 66 years Yuzhnoye SDO has developed more than 40 liquid rocket engines (LRE) of various purpose, designed both to gas-generator cycle and to staged combustion cycle. Seventeen of them were commercially produced by Yuzhmash PA and installed on launch vehicles. Nowadays Yuzhnoye propulsion experts keep working on development of the advanced liquid rocket engines powered both by cryogenic and hypergolic propellants, which satisfy the majority of launch service market demands. Within the framework of extensive cooperation with foreign space companies, on a contract basis, Yuzhnoye propulsion experts are working on the design and development testing of the liquid rocket engines, as well as their components. The accumulated vast experience in the development of liquid rocket engines nowadays enables high scientific and technical level in the creation of up-to-date engines, demanded in the world market. Significant steps in this area have been made by the experts from the Yuzhnoye propulsion division and then subsequent manufacture and delivery by Yuzhmash PA of the engine intended for the European rocket Vega Stage 4; and designing the individual components for the engines with thrusts ranging from 500 kgf to 200 tf ordered by foreign customers. This article provides the review of current and scheduled activities of the Yuzhnoye SDO to develop the liquid rocket engines within the thrust ranges from ~ 40 kgf to ~ 500 tf.
Key words: LOX-kerosene liquid rocket engines, hypergolic propellant liquid rocket engines, staged combustion cycle, main rocket engine, thrust, specific thrust impulse.
Bibliography:
- Zhidkostnye raketnye dvigateli, dvigatelnye ustanovki, bortovye istochniki moschnosti, razrabotannye KB dvigatelnykh ustanovok GP«KB «Yuzhnoye». Za nauk. red. akad. NAN Ukrainy S.M. Konyukhova, kand. tekhn. nauk V.M. Shnyakina. Dnipropetrovsk: DP «KB «Pivdenne», 2008. 466 ark.
- Prokopchyuk O. O., Shulga V. A., Khromyuk D. S., Sintyuk V. O. Zhidkostnye raketnye dvigateli GP«KB «Yuzhnoye»: nauk.-tekhn. zbirnyk. Za nauk. red. akademika NAN Ukrainy
O. V. Degtyareva. Dnipro: ART-PRES, 2019. 440 ark.
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Keywords cloud
Propulsion and Power Research.
]]>3. Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2020, (1); 26-33
DOI: https://doi.org/10.33136/stma2020.01.026
Language: Russian
Annotation: The study of thermal strength of the hold-down bay is considered. The hold-down bay is a cylindrical shell with the load-bearing elements as the standing supports. The case of the hold-down bay consists of the following structural elements: four standing supports and the compound cylindrical shell with two frames along the top and bottom joints. The purpose of this study was the development of a general approach for the thermal strength calculation of the hold-down bay. This approach includes two parts. Firstly, the unsteady heat fields on the hold-down bay surface are calculated by means of the semi-empirical method, which is based on the simulated results of the combustion product flow of the main propulsion system. The calculation is provided by using Solid Works software. Then the unsteady stress-strain behavior of the hold-down bay is calculated, taking into consideration the plastoelastic deformations. The material strain bilinear diagram is used. The finiteelement method is applied to the stress-strain behavior calculation by using NASTRAN software. The thermal field is assumed to be constant throughout the shell thickness. As a result of the numerical simulation the following conclusions are made. The entire part of the hold-down bay, which is blown by rocket exhaust jet, is under stress-strain behavior. The stresses of the top frame and the shell are overridden the breaking strength that caused structural failure. The structure of the hold-down bay, which is considered in the paper, is unappropriated to be reusable. The hold-down bay should be reconstructed by reinforcement in order to provide its reusability.
Key words: stress-strain behavior, finite-element method, plastoelastic deformations, breaking strength, reusability
Bibliography:
1. Elhefny A., Liang G. Stress and deformation of rocket gas turbine disc under different loads using finite element modeling. Propulsion and Power Research. 2013. № 2. P. 38–49. https://doi.org/10.1016/j.jppr.2013.01.002
2. Perakis N., Haidn O. J. Inverse heat transfer method applied to capacitively cooled rocket thrust chambers. International Journal of Heat and Mass Transfer. 2019. № 131. P. 150–166. https://doi.org/10.1016/j.ijheatmasstransfer.2018.11.048
3. Yilmaz N., Vigil F., Height J., et. al. Rocket motor exhaust thermal environment characterization. Measurement. 2018. № 122. P. 312–319. https://doi.org/10.1016/j.measurement.2018.03.039
4. Jafari M. Thermal stress analysis of orthotropic plate containing a rectangular hole using complex variable method. European Journal of Mechanics A /Solids. 2019. № 73. P. 212–223. https://doi.org/10.1016/j.euromechsol.2018.08.001
5. Song J., Sun B. Thermal-structural analysis of regeneratively cooled thrust chamber wall in reusable LOX / Methane rocket engines. Chinese Journal of Aeronautics. 2017. № 30. P. 1043–1053.
6. Ramanjaneyulu V., Murthy V. B., Mohan R. C., Raju Ch. N. Analysis of composite rocket motor case using finite element method. Materials Today: Proceedings. 2018. № 5. P. 4920–4929.
7. Xu F., Abdelmoula R., Potier-Ferry M. On the buckling and post-buckling of core-shell cylinders under thermal loading. International Journal of Solids and Structures. 2017. № 126–127. P. 17–36.
8. Wang Z., Han Q., Nash D. H., et. al. Thermal buckling of cylindrical shell with temperature-dependent material properties: Conventional theoretical solution and new numerical method. Mechanics Research Communications. 2018. № 92. P. 74–80.
9. Duc N. D. Nonlinear thermal dynamic analysis of eccentrically stiffened S-FGM circular cylindrical shells surrounded on elastic foundations using the Reddy’s third-order shear de-formation shell theory. European Journal of Mechanics A /Solids. 2016. № 58. P. 10–30.
10. Trabelsi S., Frikha A., Zghal S., Dammak F. A modified FSDT-based four nodes finite shell element for thermal buckling analysis of functionally graded plates and cylindrical shells. Engineering Structures. 2019. № 178. P. 444–459.
11. Trinh M. C., Kim S. E. Nonlinear stability of moderately thick functionally graded sandwich shells with double curvature in thermal environment. Aerospace Science and Technology. 2019. № 84. P. 672–685.
12. Лойцянский Л. Г. Механика жидкости и газа. М., 2003. 840 с.
13. Launder B. E., Sharma B. I. Application of the energy dissipation model of turbulence to the calculation of flow near a spinning disc. International Journal of Heat and Mass Transfer. 1974. № 1. P. 131–138.
14. Михеев М. А., Михеева И. М. Основы теплопередачи. М., 1977. 345 с.
15. Малинин Н. Н. Прикладная теория пластичности и ползучести. М., 1968. 400 с.
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Keywords cloud
Hydraulic and Pneumatic Power Control System / Under the editorship of J.
]]>12. Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2017 (1); 78-83
Language: Russian
Annotation: The basic mathematical relations are considered to construct static characteristics of nozzle-shutter twostage piston pneumatic drive with the working medium – powder combustion products.
Key words:
Bibliography:
1. Oleinik V. P. et al. Static Characteristics of Gas Drive with Jet Engine / V. P. Oleinik, Y. A. Yelansky, V. N. Kovalenko, L. G. Kaluger, Е. V. Vnukov. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2015. Issue. 1. P. 21-27.
2. Kornilov Y. G. et al. Pneumatic Elements and Systems. К., 1968. 143 p.
3. Hydraulic and Pneumatic Power Control System / Under the editorship of J. Blackborn, H. Reethoff, G. L. Sherer. М., 1962. 614 p.
4. Mertaf S. A. Tutorial on the Theory of Electrohydraulic Servo Mechanism with Acceleration Control Operating in Switchover Mode. Problems of Rocket Engineering. 1961. No. 2. P. 74-95.
5. Banshtyk A. М. Electrohydraulic Servo Mechanisms with Pulse-Width Control. М., 1972. 144 p.
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The following calculations are presen ted: strength analyses with determination of case load-carrying capacity; power analyses with justification of pyro cartridge selection for pyrobolt actuation.
]]>19. Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 170-176
DOI: https://doi.org/10.33136/stma2020.01.170
Language: Russian
Annotation: The pyrobolts, or explosive bolts, belong to the pyrotechnical devices with monolithic case consisting o f the cap, as a rule with hexagonal surface, and of cylindrical part with thread. The pyrobolts are separated into parts using the pyrotechnical charge placed inside the case. Owing to the simple design, reliability and short action time, the pyrobolts have found wide application in aerospace engineering for separation of assemblies and bays, in particular, stages, head modules, launching boosters, etc. So, for example, about 400 pyrobolts are used in the Proton launch vehicle. The designs of pyrobolts are markedly different. By method of explosive substance action on case structural elements, the pyrobolts are divided into two types: the pyrobolts using the shock wave formed at detonation of brisant explosive substance for case wall destruction and the pyrobolts using the pressure of gases arising at pyrotechnical charge blasting. By method of separation into parts, they are divided into fragmenting pyrobolts with ridge-cut, with piston, and shear pyrobolts. The paper deals with the design of various types of pyrobolts, their disadvantages are considered. The Yuzhnoye SDO-developed pyrobolt of shear type with segments is presented that uses radial shear forces of segments located in the hole of cylindrical part to separate the case parts. The above segments a re actuated using a rod with sealing rings and a piston connected to the rod through a rubber gasket; the piston moves under pressure of gases formed during pyro cartridge action. The following calculations are presen ted: strength analyses with determination of case load-carrying capacity; power analyses with justification of pyro cartridge selection for pyrobolt actuation. In the developed pyrobolt of shear type with segments, the case parts are separated without considerable shock loads and without high-temperature gases and fragments release into environment, ensuring reliable separation of bays and assemblies without damaging sensitive equipment.
Key words: explosive bolt, shock wave, brisant explosive substance, pyro cartridge, electric igniting fuse, high-temperature gases
Bibliography:
1. Mashinostroenie. Entsiklopediia / А. P. Adzhian i dr.; pod red. V. P. Legostaeva. М., 2012. Т. IV-22. V 2-kh kn. Kn. 1. 925 s.
2. Bement L. J., Schimmel M. L. A Manual for Pyrotechnic Design, Development and Qualification: NASA Technical Memorandum 110172. 1995.
3. Yumashev L. P. Ustroistvo raket-nositelei (vspomagatelnye sistemy): ucheb. posob. Samara, 1999. 190 s.
4. Lee J., Han J.-H., Lee Y., Lee H. Separation characteristics study of ridge-cut explosive bolts. Aerospace Science and Technology. 2014. Vol. 39. Р. 153-168. https://doi.org/10.1016/j.ast.2014.08.016
5. Yanhua L., Jingcheng W., Shihui X., Li C., Yuquan W., Zhiliang L. Numerical Study of Separation Characteristics of Piston-Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2019/2092796
6. Yanhua L., Yuan L., Xiaogan L., Yuquan W., Huina M., Zhiliang L. Identification of Pyrotechnic Shock Sources for Shear Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2017/3846236
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Keywords cloud
Development of autonomous power engineering systems with hydrogen energy storage Authors: Shevchenko A. 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. Hydrogen technology of energy storage making use of windpower potential. (2020) "Development of autonomous power engineering systems with hydrogen energy storage" Космическая техника. "Development of autonomous power engineering systems with hydrogen energy storage" Космическая техника. quot;Development of autonomous power engineering systems with hydrogen energy storage", Космическая техника. Development of autonomous power engineering systems with hydrogen energy storage Автори: Shevchenko A. Development of autonomous power engineering systems with hydrogen energy storage Автори: Shevchenko A.
]]>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
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
3. Vozobnovliaemaia energetika. URL: https://nv.ua/tags/vozobnovljaemaja-enerhetika.htmt (access date: 27.01.2020).
4. Sherif S. A., Barbir F., Veziroglu T. N. Wind energy and the hydrogen economy-review of the technology. Solar energy. 2005. № 78(5). P. 647–660. https://doi.org/10.1016/j.solener.2005.01.002
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
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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Keywords cloud
2020, (1); 155-159 DOI: https://doi.org/10.33136/stma2020.01.155 Language: Russian Annotation: Due to an increase of power of rocket engines, the high intensity sound field generated by the exhaust jets have become an important factor, which determines the success rate of a rocket launch.
]]>17. Acoustic problems of rocket launch
Organization:
Institute of Hydromechanics of National Academy of Sciences of Ukraine, Kyiv, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 155-159
DOI: https://doi.org/10.33136/stma2020.01.155
Language: Russian
Annotation: Due to an increase of power of rocket engines, the high intensity sound field generated by the exhaust jets have become an important factor, which determines the success rate of a rocket launch. Ensuring a successful launch of a rocket system became harder due to new engineering problems. Identification and definition of acoustic sources structure within a complex supersonic jet, being a one of the most important scientific problems, which have to be solved to find the ways to control accoustic radiation. A three components of acoustic sources can be defined here – broadband signals from large and small components of of turbulent jet and tonal signals which usually being overlooked during the estimation of overall sound pressure level. The paper considers various aspects of acoustics of the launch of rocket systems, which includes characteristics of acoustic sources in supersonic jets, possibilities and physical limitation factors, under which it is possible to control the sound radiation. Among the possible ways to control the process of sound generation by a jet, a method of water injection in a jet is being studied. While saving the general thrust of the engine this method can not greatly reduce the sound radiation by a jet. It is recommended to use big amounts of water-air mix to protect the launch pad from damage. Significant progress on the topic of understanding the process of sound generation by supersonic jets can be achieved via mathematical modeling of sound radiation. The latest achievements of mathematical modeling of sound generation by supersonic jets being presented.
Key words: Acoustics of rocket launch, acoustic efficiency of a jet, semi-empirical models of of jet acoustics, numeric-computational methods in aeroacoustics, control of jet-generated acoustic levels
Bibliography:
1. Lighthill M. J. On Sound Generated Aerodynamically: I. General Theory. Proc. Roy. Soc. London Ser. A, 211. 1952. Р. 564–581. https://doi.org/10.1098/rspa.1952.0060
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