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3 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; The Institute of Technical Mechanics, Dnipro, Ukraine 2 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 3 Page: Kosm.
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5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

Authors:

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

Organization:

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

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

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

Language: Russian

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

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

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

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]]> 22.2.2017 Advanced Aluminum Alloys for Launch Vehicle Pipeline Parts Manufacture https://journal.yuzhnoye.com/content_2017_2/annot_22_2_2017-en/ Wed, 09 Aug 2023 12:36:11 +0000 https://journal.yuzhnoye.com/?page_id=29944
1 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 2 .
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22. Advanced Aluminum Alloys for Launch Vehicle Pipeline Parts Manufacture

Authors:

Bondarenko О. V.2, Mogilevtsev O. А.1, Tishchenko Y. S.1

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2.

Page: Kosm. teh. Raket. vooruž. 2017 (2); 127-130

Language: Russian

Annotation: The comparison has been made of mechanical characteristics based on yield strength values of prospective aluminum alloys and steels with the stresses arising in pipeline parts. The conclusions have been drawn about the principal feasibility of manufacturing the pipelines of given materials and replacing the steels with the high-strength aluminum alloys for majority of the parts.

Key words:

Bibliography:
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2. Alekseyev Y. S. Space Rocket Flying Vehicles Manufacturing Technology: Tutorial / Y. S. Alekseyev, E. O. Dzhur, О. V. Kulik, L. D. Kuchma, E. Y. Nikolenko, V. V. Khutorny / Under the editorship of E. O. Dzhur, Doctor of Engineering Science. Dnipropetrovsk, 2007. 480 p.
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22.2.2017 Advanced Aluminum Alloys for Launch Vehicle Pipeline Parts Manufacture
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22.2.2017 Advanced Aluminum Alloys for Launch Vehicle Pipeline Parts Manufacture
]]> 21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft https://journal.yuzhnoye.com/content_2017_2/annot_21_2_2017-en/ Wed, 09 Aug 2023 12:32:56 +0000 https://journal.yuzhnoye.com/?page_id=29940
2 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 2 Page: Kosm.
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21. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft

Authors:

Husarova I. O.1, Potapov O. М.1, Shevtsov E. I.1, Onofriienko V. I.1, Husev V. V.1, Manko Т. А.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2017 (2); 121-126

Language: Russian

Annotation: The paper considers the TZS-U design developed by Yuzhnoye SDO specialists for windward part of reusable spacecraft with external metal three-layer panel, U-like joint and tiled thermal protection, in which the problem is solved of compensation of thermal expansions and sealing of gaps; for optimization of structural mass. The specially created dispersion-hardened powder alloy based on nichrome and aluminum with yttrium dioxide with decreased specific mass of 7500 kg/m3 and lighter felt of MKRF brand are used , and honeycomb filler of three-layer panel is replaced by the filler with square cell.

Key words:

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21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft
21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft
21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft
]]> 6.1.2017 Drought Post-Effects Satellite Monitoring https://journal.yuzhnoye.com/content_2017_1/annot_6_1_2017-en/ Tue, 27 Jun 2023 12:02:02 +0000 https://journal.yuzhnoye.com/?page_id=29420
2 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 2 Page: Kosm.
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6. Drought Post-Effects Satellite Monitoring

Authors:

Masley V. M.1, Belousov К. G.1, Khoroshilov V. S.1, Bushanskaya O. S.1, Mozgovoy D. К.2, Vasilyev V. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2017 (1); 35-42

Language: Russian

Annotation: The analysis of medium- and high-resolution satellite images is made for the purpose of evaluating the impact of 2011-2015 drought on large freshwater basins of California. The considerable coast line shifts of Oroville and Folsom lakes were revealed.

Key words:

Bibliography:
1. Mozgovoy D. K., Voloshin V. I. Coastline Imaging Technique. Collection of abstracts of the 6th Ukrainian Conference on Space Research (Crimea, Yevpatoriya, NTsUIKS, 3-10 September, 2006). NASU-SSAU Space Research Institute, 2006. P. 136.
2. Mozgoviy D. K., Parshina O. I., Voloshin V. I., Bushuev Y. I. Remote Sensing and GIS Application for Environmental Monitoring and Accidents Control in Ukraine. Geographic Uncertainty in Environmental Security / Edited by A. Morris, S. Kokhan. Dordrecht, 2007. P. 259-270.
3. Mozgovoy D. K., Voloshin V. I. Coastal Zones Imaging Technology. Present-Day Problems of Rational Nature Management in Sea Offshore Strips of Ukraine: Abstracts of papers for the International Conference of Young Scientists (Sevastopol – Katsiveli, 12-14 June, 2007). Sevastopol, 2007. P. 21-22.
4. Mozgovoy D. K. Use of Earth Observation Data for Natural Resources Monitoring. Scientific Readings “Space Technologies for the Benefit of Sustainable Development and Security of Society” (National Center of Aerospace Education of the Youth of Ukraine, Dnipropetrovsk, 18 May, 2007). Dnipropetrovsk, 2007. http://www.festival.nas.gov.ua/2007/Measures/ Pages/1062.aspx.
5. Mozgovoy D. K Increase of Information Capacity of Satellite Imaging of Small-Size Objects on Earth Surface. Program of Scientific Conference on results of research work of the University in 2012. Dnipropetrovsk, 2012. P. 92.
6. Mozgovoy D. K. Satellite Images Processing when Solving Applied Tasks. Abstract of paper for the International Scientific-Practical Forum “Science and Business” (29-30 June, 2015, Dnipropetrovsk, Noosphere Ventures inc.). P. 191-194.
7. Mozgovoy D. K. Satellite Monitoring of Forest Fires and Droughts. Abstract of paper for the International Scientific-Practical Conference “Advanced Methods Space Information Processing and Analysis” (3-4 December, 2015, Dnipropetrovsk, Noosphere Ventures inc.). P. 48-53.
8. Mozgovoy D. K., Vasilyev V. V. Analysis of Multiyear Drought Based on Landsat-8 Data. DNU concl. Space Rocketry. 2016. Issue 13, Vol. 24. No. 4. P. 79-89.
9. Mozgovoy D. K. Monitoring of Droughts Consequence by High Resolution Satellite Images. Ecology and Noospherology. 2016. Vol. 27, No. 1-2. P. 89-90.
10. Mozgovoy D. K. Monitoring of Droughts Consequence by High Resolution Satellite Images. Ecology and Noospherology. Vol. 27, No. 1-2. Kyiv – Dnipropetrovsk, 2016. P. 90-95.

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]]> 4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle https://journal.yuzhnoye.com/content_2017_1/annot_4_1_2017-en/ Thu, 22 Jun 2023 12:38:35 +0000 https://journal.yuzhnoye.com/?page_id=29370
2 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 2 Page: Kosm.
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4. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle

Authors:

Husarova I. O.1, Potapov O. М.1, Golubkov G. М.1, Kalinichenko D. S.1, Poluyan M. V.1, Manko Т. А.2

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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4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
]]> 14.2.2016 Investigation of Deformability of Carbon Plastic Panels in Moisture Absorption Process https://journal.yuzhnoye.com/content_2016_2-en/annot_14_2_2016-en/ Tue, 06 Jun 2023 12:03:05 +0000 https://journal.yuzhnoye.com/?page_id=28329
1 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 2 Page: Kosm.
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14. Investigation of Deformability of Carbon Plastic Panels in Moisture Absorption Process

Authors:

Vaisero M. V.1, Kavun V. V.1, Kudrevatykh А. Т.2, Moskalyov S. I.1, Rozhkovsky V. F.2, Sokhach Y. V.2, Shchudro A. P.1

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2016 (2); 85-91

Language: Russian

Annotation: The developed technology for experimental estimation of stability of sizes of carbon structures in the process of moisture absorption is under consideration. The results of geometry change of honeycomb carbon panel at its imbibition are described.

Key words:

Bibliography:

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14.2.2016 Investigation of Deformability of Carbon Plastic Panels in Moisture Absorption Process
14.2.2016 Investigation of Deformability of Carbon Plastic Panels in Moisture Absorption Process
14.2.2016 Investigation of Deformability of Carbon Plastic Panels in Moisture Absorption Process
]]> 3.2.2016 Selection of Optimal Trajectories of Spacecraft Launch Vehicles https://journal.yuzhnoye.com/content_2016_2-en/annot_3_2_2016-en/ Tue, 06 Jun 2023 11:48:34 +0000 https://journal.yuzhnoye.com/?page_id=28306
1 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 2 Page: Kosm.
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3. Selection of Optimal Trajectories of Spacecraft Launch Vehicles

Authors:

Kompaniyets E. P.1, Dron’ M. M.2, Baranov E. Y.1, Litvin M. G.1

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2016 (2); 17-29

Language: Russian

Annotation: An analysis of the existing methods of trajectories selection of spacecraft launch vehicles is performed. A generalized method is proposed for selection of optimal flight trajectories of launch vehicles in the central gravitational field when launching the artificial earth satellites.

Key words:

Bibliography:

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3.2.2016 Selection of Optimal Trajectories of Spacecraft Launch Vehicles
3.2.2016 Selection of Optimal Trajectories of Spacecraft Launch Vehicles
3.2.2016 Selection of Optimal Trajectories of Spacecraft Launch Vehicles
]]> 9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source https://journal.yuzhnoye.com/content_2019_1-en/annot_9_1_2019-en/ Thu, 25 May 2023 12:09:50 +0000 https://journal.yuzhnoye.com/?page_id=27714
2 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 2 Page: Kosm.
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9. Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source

Authors:

Sirenko V. M.1, Sokol G. I.2, Savchuk V. M.1, Kotlov V. Y.2, Savchuk T. L.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2019, (1); 64-71

DOI: https://doi.org/10.33136/stma2019.01.064

Language: Russian

Annotation: During lift-off of integrated launch vehicles, the propulsion system jet generates acoustic field. Therewith, the loads can be created that are critical for the launching equipment, rocket body and especially for the spacecraft, which are under the fairing. To take into account the effects on these elements, it is necessary to determine the characteristics of generated acoustic field. The method was developed that allows modeling the acoustic fields during integrated launch vehicle lift-off based on determination of acoustic sources type. In particular, modeling of Cyclone-4M ILV jet acoustic radiation by bulky source was performed. This provided the possibility to calculate acoustic pressure amplitudes in ILV ambient medium and to evaluate acoustic effect on the rocket body at certain points. The method is expected to be used to investigate kR wave parameter. The modeling of integrated launch vehicle propulsion system (ILV PS) jet acoustic field as bulky radiation source was performed in the rocket flight leg where ILV ascent altitude does not exceed ~ 25 m. In this case, one should be based on the value of boundary frequency fb =150 Hz which separates two types of acoustic field: fb ˂ 150 Hz – front of acoustic wave of spherical type, fb > 150 Hz – front of acoustic wave of flat type. The algorithm and program of calculation of sound pressure levels were developed in JAVA language. The characteristics of acoustic fields sound pressure levels were calculated depending on radiation frequency taking into account environmental temperature. The maximal acoustic pressure level in 150 Hz frequency in the payload area outside the fairing – 155 dB, in the instrumentation bay area – 157 dB, in the intertank bay area – 172 dB, in the aft bay area – 182 dB. In the frequencies lower than 150 Hz, the sound pressure levels are lower. The calculation data are presented graphically.

Key words: integrated launch vehicle, acoustic field, sound pressure

Bibliography:

1. Dementiev V. K. O maximalnykh akusticheskykh nagruzkakh na rekety pri starte/ V. K. Dementiev, G. Ye. Dumnov, V. V. Komarov, D.A. Melnikov// Kosmonavtika I raketostroenie. 2000. Vyp. 19. P. 44-55.
2. Tsutsumi S., Ishii T., Ut K., Tokudone S., Chuuouku Y., Wado K. Acoustic Design of Launch Pad for Epsilon Launch Vehicle / Proceedings of AJCPP2014 . Asian Joint Conference on Propulsion and Power, March 5- 8, 2014, Jeju Island, Korea. AJCPP2014-090.
3. Panda J., Mosher R., Porter D.J. Identification of Noise Sources during Rocket Engine Test Firings and a Rocket Launch a Microphone Phased-Array // NASA / TM2013-216625, December 2013. P. 1-20.
4. Sokol G. I. Metod opredeleniya vida istochnikov akusticheskogo izlucheniya v pervye secundy starta raket kosmicheskogo naznacheniya/ G. I. Sokol// Systemne proektuvannya ta analiz characteristic aerokosmichoi techniki: Zb. nauk. pr. 2018. XXIV. Dnipro: Lira, 2018. P. 91-101.
5. Sokol G. I., Frolov V. P., Kotlov V. Yu. / Volnovoy parameter kak kriteriy v osnove metoda issledovaniya akusticheskikh istochnikov pro starte raket/ Aviatsionno-kosmicheskaya technika I technologia. 2018. 3 (147), May-June 2018. Kharkov: KhAI, 2018. P. 4-13. DОІ:http://doi.org /10.20535/0203- 3771332017119600.
6. Rzhevkin S. N. Kurs lektsiy po teorii zvuka/ S. N. Rzhevkin. M.: MGU, 1960. 261 p.
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12. Schildt G. Java 8. Polnoe rukovodstvo. 9-e izd. M.: Wiliams, 2015. 137 p.

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9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source
9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source
9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source

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]]> 5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime https://journal.yuzhnoye.com/content_2019_1-en/annot_5_1_2019-en/ Thu, 25 May 2023 12:09:25 +0000 https://journal.yuzhnoye.com/?page_id=27710
3 Organization: The Institute of Technical Mechanics, Dnipro, Ukraine 1 ; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 2 ; Oles Honchar Dnipro National University, Dnipro, Ukraine 3 Page: Kosm.
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5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

Authors:

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

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2019, (1); 28-37

DOI: https://doi.org/10.33136/stma2019.01.028

Language: Russian

Annotation: This article contains results of methodology and standards development for life prediction of launch site structures to launch various types’ launch vehicles into near-earth orbit. Launch sites have been built in various countries of the world (European Union, India, China, Korea, Russia, USA, Ukraine, France, Japan, etc.). In different countries they have their own characteristics, depending on the type and performance of the launch vehicles, infrastructure features (geography of the site, nomenclature of the space objects, development level of rocket and space technology), problems that are solved during launches, etc. Solution of various issues, arising in the process of development of the standards for justification of launch site life is associated with the requirement to consider complex problems of strength and life of nonuniform structural elements of launch sites and structures of rocket and space technology. Launch sites are the combination of technologically and functionally interconnected mobile and fixed hardware, controls and facilities, designed to support and carry out all types of operations with integrated launch vehicles. Launch pad, consisting of the support frame, flue duct lining and embedded elements for frame mounting, is one of the principal components of the launcher and to a large extent defines the life of the launch site. Main achievements of Ukrainian scientists in the field of strength and life are specified, taking into account the specifics of various branches of technology. It is noted that the physical nonlinearity of the material and statistical approaches determine the strength analysis of useful life. Main methodological steps of launch site structures life prediction are defined. Service limit of launch site is suggested to be the critical time or the number of cycles (launches) over this period, after which the specified limiting states are achieved in the dangerous areas of the load-bearing elements: critical cracks, destruction, formation of unacceptable plastic deformations, buckling failure, corrosion propagation, etc. Classification of loads acting on the launch sites is given. The useful life of launch site is associated with estimation of the number of launches. Concept of low and multiple-cycle fatigue is used. Developing strength standards and useful life calculation basis, it is advisable to use modern methods of engineering diagnostics, in particular, holographic interferometry and acoustic emission, and to develop the high-speed circuits of numerical procedures for on-line calculations when testing the designed systems.

Key words: classification of loads and failures; shock wave, acoustic and thermal loads; low-cycle fatigue; hierarchical approach in classification; projection-iterative schemes of numerical procedur

Bibliography:

1. Vidy startovykh kompleksov: GP KB «Yuzhnoye»: Rezhim dostupa. http://www.yuzhnoe.com/presscenter/media/ photo/techique/launch-vehique.
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5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

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]]> 27.1.2019 Phases of Cooperation of Yuzhnoye SDO and Dnipro National University Physical Engineering Department on the Issues of Mutual Human Resourcing: Past, Present. Future https://journal.yuzhnoye.com/content_2019_1-en/annot_27_1_2019-en/ Wed, 24 May 2023 16:01:14 +0000 https://journal.yuzhnoye.com/?page_id=27732
Organization: Oles Honchar Dnipro National University, Dnipro, Ukraine Page: Kosm.
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27. Phases of Cooperation of Yuzhnoye SDO and Dnipro National University Physical Engineering Department on the Issues of Mutual Human Resourcing: Past, Present. Future

Authors:

Linnik A. K.

Organization:

Oles Honchar Dnipro National University, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 188-194

DOI: https://doi.org/10.33136/stma2019.01.189

Language: Russian

Annotation: This paper in brief presents the history of cooperation between the Yuzhnoye State Design Office (YSDO) and University’s applied-physics faculty focused on drawing the enterprise specialists to teaching activity at the faculty, and University graduates – to work at the enterprise. Interchange of personnel throughout three periods is analyzed: a) in the remote past (early 1950s – late 1980s); b) watershed years at the turn of millennia (early 1990s – mid 2010s) and c) nowadays (from mid 2010s). Forecast attempt for the near future is also made. Active participation of the outstanding YSDO specialists in the organization and education at the faculty, especially at the first stage of cooperation, is shown. In particular, Y. A. Smetanin, YSDO Deputy General Designer, was the head of department №1, N. S. Shnyakin was the head of department №2, department №3 was chaired by N. F. Gerasyuta – Head of Dynamics, Ballistics and Control Department in YSDO. At that period faculty trained annually all in all ~300 young specialists for Yuzhnoye State Design Office. Great deal of problems and new challenges, which emerged in watershed 1990s, are described. Despite this, close cooperation between the YSDO and faculty was basically maintained. Thus, for example, for several years S. N. Konyukhov, YSDO General Designer, chaired the state examination board on defence of graduation works of the department №1 students. At the same time, number of aerospace specialties graduates this period has sharply decreased to 35 graduates. The present state of affairs, causing concern, is shown. Actual admission rate for the aerospace specialties for the past years suggests that starting with 2022, number of graduates for Yuzhnoye State Design Office can practically reduce to nothing.

Key words: cooperation, enterprise, faculty, staff, experts, graduates, students, applicants

Bibliography:
1. Sekretniy pidrozdil galuzi: Narysy istorii physiko-technochnogo institute Dnipropetrovskogo natsionalnogo universitetu; M. V. Polyakov (kerivnik redkol). D.: Bid-vo Dnipropetr. un-tu. 2001. 376 p.
2. Kafedra kosmicheskikh informatsionnykh technologiy/ www.fti.dnu.
3. Strategichniy plan rozvytku DP KB “Pivdenne” na 2017-2021.

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27.1.2019 Phases of Cooperation of Yuzhnoye SDO and Dnipro National University Physical Engineering Department on the Issues of Mutual Human Resourcing: Past, Present. Future
27.1.2019 Phases of Cooperation of Yuzhnoye SDO and Dnipro National University Physical Engineering Department on the Issues of Mutual Human Resourcing: Past, Present. Future
27.1.2019 Phases of Cooperation of Yuzhnoye SDO and Dnipro National University Physical Engineering Department on the Issues of Mutual Human Resourcing: Past, Present. Future

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