Search Results for “computational experiment” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Mon, 16 Mar 2026 17:48:31 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “computational experiment” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 1.2.2025 Methods for structural strength investigations of rocketry. https://journal.yuzhnoye.com/content_2025_2-en/annot_1_2_2025-en/ Tue, 27 Jan 2026 01:13:55 +0000 https://journal.yuzhnoye.com/?page_id=35812
An analysis of the calculated values of the model’s stress and strain is performed based on the results of the computational experiment, and the critical regions within the structure are determined, where these parameters reach their peak values. A predicted structural failure load is found by comparing the strain and translation values obtained from the test results with the outputs of computational experiments. Key words: strength , fi nite element method , computational experiment , strength testing Bibliography: 1. strength , fi nite element method , computational experiment , strength testing .
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1. Methods for structural strength investigations of rocketry.

Date of receipt of the article for publication: 31.10.2025

Date of acceptance of the article for publication after review: 14.11.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Drobenko B. D.1, Klymenko D. V.1, Kushnir R. M.1, Marchuk M. V.1, Sirenko V. M.2, Kharchenko V. M.2

ORCID authors:

Drobenko B. D.1 ORCID, Klymenko D. V.1 ORCID, Kushnir R. M.1 ORCID, Marchuk M. V.1 ORCID, Sirenko V. M.2 ORCID, Kharchenko V. M.2 ORCID

Organization:

Ya. S. Pidstryhach Institute for Applied Problems of Mechanics and Mathematics of the National Academy of Sciences of Ukraine1, Yangel Yuzhnoye State Design Office2

Page: Kosm. teh. Raket. vooruž. 2025 (1); 3-11

DOI: https://doi.org/10.33136/stma2025.02.003

Language: Ukrainian

Annotation: The paper proposes a method for investigating structural strength and determining structural failure loads by computer-aided simulation and nondestructive testing. The methodology is grounded on general ratios of elastoplasticity in increments based on the Lagrangian approach and the principle of virtual translations, taking into account the geometrically nonlinear nature of structural deformation under intense loading. The baseline technique for numerical simulation was the fi nite element method. The methodology for structural strength investigation includes three steps. The fi rst step involves studying the structure in the form of a spatially two-dimensional shell-like model. An analysis of the calculated values of the model’s stress and strain is performed based on the results of the computational experiment, and the critical regions within the structure are determined, where these parameters reach their peak values. The second step yields detailed three-dimensional models of those critical regions within the structure. These models incorporate the geometrical (including the actual thicknesses of the elements) and physical specifi cs of the structure. The results of numerical experiments are applied in an analysis of the refi ned stress and strain values of the three-dimensional models, and the minimum structural failure load is determined. In the third step, strain gauges are installed in the determined critical regions, and the structure’s strength is tested using a nondestructive load. A predicted structural failure load is found by comparing the strain and translation values obtained from the test results with the outputs of computational experiments. The development of the mentioned methodology encompassed an investigation of stress and strain at diff erent internal pressures for an oxidizer tank of a launch vehicle’s fi rst stage, a quantitative estimation of the tank’s strength, and the determination of the structural failure load and regions where a structural failure is likely to start. This paper demonstrates that the results of a tank strength analysis using a criterion of a maximum stress are closest to experimental data.

Key words: strength, fi nite element method, computational experiment, strength testing

Bibliography:

1. Allen D.H., Heisler W. E. A theory for analysis of thermoplastic materials. Computers & Structures. 1981. Vol. 13. P. 129-135 https://doi.org/10.1016/0045-7949(81)90117-6
2. Bathe K.J. Finite Element Procedures Analysis. Englewood Cliffs: Prentice Hall, 1995. 1037 p.
3. Zienkiewicz O.C., Taylor R.L. Finite Element Method: Vol.1. The Basis. London: Butterworth Heinemann, 2000. 689 p.
4. Hachkevich O.P., Drobenko B.D. Modeliuvannia ta optymizatsiia v termomekhanitsi elektroprovidnykh neodnoridnykh til. Pid zah. red. Ya. Y. Buraka, R.M. Kushnira. T. 4: Termomekhanika namahnechuvanykh elektroprovidnykh termochutlyvykh til. Lviv: SPOLOM, 2010.256 s.
5. Kleiber M. Incremental Finite Element Modelling in Non-Linear Solid Mechanics. John Wiley & Sons, 1989. 187 p.
6. Computational Methods for Nonlinear Problems. Ed. by Taylor C., Owen D. R. J., Hinton E. Swansea: Pineridge Press, 1987. 384 p.
7. Marchuk M.V. Neliniine deformuvannia podatlyvykh transversalnym deformatsiiam zsuvu ta stysnennia plastyn i obolonok. Mashynoznavstvo. 2005. № 10. S. 9-14.

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]]> 3.1.2025 Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks https://journal.yuzhnoye.com/content_2025_1-en/annot_3_1_2025-en/ Wed, 27 Aug 2025 12:40:38 +0000 https://journal.yuzhnoye.com/?page_id=35481
A Computational and Experimental Analysis of Spacecraft Propellant Tanks Implemented with Flexible Diaphragms.
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3. Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks

ISSN: 2617-5525

e-ISSN: 2617-5533

Автори: Shulha V. A., Pidhainyi A. I., Mudrov D. S.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2025 (1); 19-27

DOI: https://doi.org/10.33136/stma2025.01.019

Language: Ukrainian

Annotation: This paper presents the results of comprehensive research on the operational performance of diaphragm separators utilized in the fuel storage and supply systems for liquid-propellant rocket engines (LPRE). The relevance of this study arises from the need to ensure the reliable separation of gas and liquid duringthe operation of aerospace systems under diff erent conditions. In this context, special attention is given to autonomous bench tests that enable the evaluation of the key performance parameters of diaphragms before integrating them into production models. The paper examines the shape transformation of spherical diaphragms under external loads, presents an analytical calculation of the initial diaphragm inversion radius, and identifi es the critical pressures that cause buckling. The results of this calculation demonstrate a satisfactory correlation with the experimental data obtained during testing. The methodology for qualifi cation tests conducted on fi ve diff erent diaphragm variants is described. Several technological and design measures have been implemented to enhance product quality. They included increasing the number of drawing passes from two to three with intermediate annealing, reducing the thickness of the blanks, and enlarging the non-rolled polar zone. It was found that the primary factor ensuring defect-free diaphragm inversion is the reduced number of roller passings along the diaphragm contour, which prevents the tearing of the surface layer. The test results for diff erent diaphragm variants confi rmed satisfactory performance. An analysis of pressure diff erentials across the diaphragms during inversion confi rmed compliance with the technical specifi cations. The study concluded that the diaphragm design, when it incorporates all corrective measures, ensures defect-free inversion while maintaining the required pressure diff erential and is recommended for further testing as part of standard tank assemblies.

Key words: Strength parameters; aircraft, space and rocket technologies; design parameters; mathematical simulation; fuel tank; separation diafragm; autonomous bench testing; critical pressure

Bibliography:

1. Ballinger I. A., Lay W. D., Tam W. H. Review and History of PSI Elastomeric Diaphragm Tanks. 31st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 10-12
July 1995, San Diego, CA, USA. DOI: https://doi.org/10.2514/6.1995-2534.

2. Hartwig J. W. A detailed historical review of propellant management devices for low gravity propellant acquisition. 52nd AIAA/SAE/ASEE Joint Propulsion Conference,
25-27 July 2016, Salt Lake City, USA. Reston: American Institute of Aeronautics and Astronautics. DOI: https://doi.org/10.2514/6.2016-4772.

3. Lenahen B., Gangadharan S., Desai M. A Computational and Experimental Analysis of Spacecraft Propellant Tanks Implemented with Flexible Diaphragms. Proceedings of
the 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Boston, Massachusetts, USA: American Institute of Aeronautics and
Astronautics. DOI: https://doi.org/10.2514/6.2013-1886.

4. Sabaghzadeh H., Shafaee M. Reversal modeling and optimal design of hyper-elastic diaphragm in space fuel tanks. SN Applied Sciences. 2021. Vol. 3, Article number:
792. DOI: https://doi.org/10.1007/s42452-021-04785-0

5. Conomos H. A., Alongi C. G., Moore J., Yager J., Goddard R., Salzler T., Fetes J., Burch K. Development of 10 inch Diameter Titanium Rolling Metal Diaphragm Tank
for Green Propellant. AIAA Propellant Storage and Management II. DOI: https://doi.org/10.2514/6.2017-4915.

6. Jøraholmen T., Korsvold S., Sandvold P., Luktvasslimo Ø., Snilsberg K. E.
Roadmap towards a qualified aluminium green propellant diaphragm tank. Aerospace Europe Conference 2023 – 10ᵀᴴ EUCASS – 9ᵀᴴ CEAS, 9-13 July 2023, Lausanne, Switzerland.
Lausanne: EUCASS. DOI: https://doi.org/10.13009/EUCASS2023-093.

7. Shen Y. A computational analysis of reversal behaviors of a spacecraft propellant management device. International Conference Optoelectronic Information and Optical
Engineering (OIOE 2024), 2024, Wuhan, China. Bellingham: SPIE, 2025. (Proceedings of SPIE; Vol. 13513). DOI: https://doi.org/10.1117/12.3045569.

8. Windisch M., Beck R. Numerical Simulation and Optimisation of a Hemisсherical Metallic Membrane Designed for Positive Expulsion of a Propellant Tank (for
Replacement of Conventional PMD). Spacecraft Structures, Materials and Mechanical Testing: Proceedings of a European Conference, 4-6 November 1998, Braunschweig,
Germany. Paris: European Space Agency (ESA), 1999. Vol. 428. P. 45. ISBN 9290927127.

9. Mudrov D.S., Zil V.V. Doslidzhennia napruzheno-deformovanoho stanu vytysknykh diafrahm. Heotekhnichna mekhanika: zb. nauk. prats. / In-t heotekh. mekh. im. M.S.
Poliakova NAN Ukrainy. Dnipro, 2016. Vyp. 131. S. 173-182.

10. Mozharovskii M.S. Teoriia pruzhnosti, plastychnosti i povzuchosti: pidruchnyk / M.S. Mozharovskyi. K. : Vyshcha shkola, 2002. 308 s.

11. Libai A., Simmonds J.G. The Nonlinear Theory of Elastic Shells. 2nd ed. Cambridge: Cambridge University Press, 1998. 564 p. ISBN 978-0-521-01976-7.

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3.1.2025 Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks
3.1.2025 Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks
3.1.2025 Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks

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]]> 4.1.2024 The dynamics of servo drives https://journal.yuzhnoye.com/content_2024_1-en/annot_4_1_2024-en/ Wed, 12 Jun 2024 16:08:46 +0000 https://journal.yuzhnoye.com/?page_id=34978
To describe the effect of gap in the kinematic connection the special computational trick, which considerably simplifies its mathematical description, is used. 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.
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4. The dynamics of servo drives

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Degtiarov М. O., Karpenko V. Y., Kozak L. R.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

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:
  1. Kozak L. Dynamika servomechanismov raketnoy techniki. Inzhenernye metody issledovaniya. Izd-vo LAP LAMBERT Academic Publiching, Germania. 2022.
  2. Kozak L. R., Shakhov M. I. Matematicheskie modely hydravlicheskikh servomekhanismov raketno-kosmicheskoy techniki. Kosmicheskaya technika. Raketnoe vooruzhenie. 2019. Vyp. 1.

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]]> 10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests https://journal.yuzhnoye.com/content_2018_2-en/annot_10_2_2018-en/ Thu, 07 Sep 2023 11:29:45 +0000 https://journal.yuzhnoye.com/?page_id=30766
The use the flow model k-ω SST for calculation of nozzle with flow separation or with internal transitional layer allows adequately describing the flow pattern, though, as the comparison with experimental data showed, this model predicts later flow separation from the wall than that obtained in the tests. Experimental Investigation of Exhaust Diffusors for Rocket Engines. Computational Hydromechanics and Heat Exchange: in 2 volumes М., 1990. Experimental Investigation of Heat Exchange and Critical Heat Loads at Water Boiling in Free Motion Conditions.
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10. Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Nikitenko K. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 83-93

DOI: https://doi.org/10.33136/stma2018.02.083

Language: Russian

Annotation: At Yuzhnoye State Design Office, the Cyclone-4 launch vehicle 3rd stage engine has been developed and is under testing. For adjustment of the engine and test bench systems, in the first firing tests the radiation-cooled nozzle extension was replaced with a steel water-cooled one. It was planned to start the engine with water-cooled nozzle extension without vacuumizing and without gad dynamic pipe, which conditioned operation with flow separation at the output edge of water-cooled nozzle extension. Therefore, the calculation of flow in the nozzle with water-cooled extension, flow separation place, and thermal load on watercooled nozzle extension during operation in ground conditions is an important task. Selection of turbulent flow model has a noticeable impact on prediction of flow characteristics. The gas dynamic analysis of the nozzle with water-cooled extension showed the importance of using the turbulent flow model k-ω SST for the flows with internal separation of boundary layer and with flow separation at nozzle section. The use the flow model k-ω SST for calculation of nozzle with flow separation or with internal transitional layer allows adequately describing the flow pattern, though, as the comparison with experimental data showed, this model predicts later flow separation from the wall than that obtained in the tests. The calculation allows obtaining a temperature profile of the wall and providing the recommendations for selection of pressure measurement place in the nozzle extension for the purpose of reducing sensors indication error. With consideration for the special nature of the nozzle extension wall temperature field, the cooling mode was selected. The tests of RD861K engine nozzle with water-cooled extension allow speaking about its successful use as a required element for testing engine start and operation in ground conditions without additional test bench equipment.

Key words: turbulent flow, flow separation, cooling, technological extension

Bibliography:
1. Massiet P., Rocheque E. Experimental Investigation of Exhaust Diffusors for Rocket Engines. Investigation of Liquid Rocket Engines. М., 1964. P. 96-109.
2. Mezhevov A. V., Skoromnov V. I., Kozlov A. V. et al. Introduction of Radiation Cooling Nozzle Head of Made of Carbon-Carbon Composite Material on DM-SL Upper Stage 11D58M Main Engine. News of Samara Aerospace University. No. 2 (10). 2006. P. 260-264.
3. Fluent. Software Package, Ver. 6.2.16, Fluent Inc., Lebanon, NH, 2004.
4. Wilcox D. C. Turbulence Modeling for CFD. DCW Industries, Inc. La Canada, California, 1998. 460 р.
5. Andersen D., Tannehill J., Platcher R. Computational Hydromechanics and Heat Exchange: in 2 volumes М., 1990. 384 p.
6. Rodriguez C. G., Culter, A. D. Numerical Analysis of the SCHOLAR Supersonic Combustor, NASA-CR-2003-212689. 2003. 36 р.
7. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952
8. Spalart P., Allmaras S. A one-equation turbulence model for aerodynamic flows: Technical Report. American Institute of Aero-nautics and Astronautics. AIAA-92-0439. 1992. Р. 5-21. https://doi.org/10.2514/6.1992-439
9. Launder B. E., Spalding D. B. Lectures in Mathematical Models of Turbulence. London, 1972. Р. 157-162.
10. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952
11. Ten-See Wang. Multidimensional Unstructured Grid Liquid Rocket-Engine Nozzle Performance and Heat Transfer Analysis. Journal of Propulsion and Power. Vol. 22. No. 1. 2006. 21 р. https://doi.org/10.2514/1.14699
12. Hyun Ko, Woong-Sup Yoon. Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle. Journal of Propulsion and Power. Vol. 18, No. 3. 2002. Р. 585-591. https://doi.org/10.2514/2.5972
13. Wilson E. A., Adler D., Bar-Yoseph P. Thrust-Vectoring Nozzle Performance Mode-ling. Journal of Propulsion and Power. Vol. 19, No. 1. 2003. Р. 39-47. https://doi.org/10.2514/2.6100
14. Gross A., Weiland C. Numerical Simulation of Hot Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 5. 2004. Р. 879-891. https://doi.org/10.2514/1.5001
15. Gross A., Weiland C. Numerical Simulation of Separated Cold Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 3. 2004. Р. 509-519. https://doi.org/10.2514/1.2714
16. Deck S., Guillen P. Numerical Simulation of Side Loads in an Ideal Truncated Nozzle. Journal of Propulsion and Power. Vol. 18, No. 2. 2002. Р. 261-269. https://doi.org/10.2514/2.5965
17. Östlund J., Damgaard T., Frey M. Side-Load Phenomena in Highly Overexpanded Rocket Nozzle. Journal of Propulsion and Power. Vol. 20, No. 4. 2004. Р. 695-704. https://doi.org/10.2514/1.3059
18. Goldberg U. C. Separated Flow Treatment with a New Turbulence Model. AIAA Journal. Vol. 24, No. 10. 1986. Р. 1711-1713. https://doi.org/10.2514/3.9509
19. Golovin V.S., Kolchugin B.A., Labuntsov D.A. Experimental Investigation of Heat Exchange and Critical Heat Loads at Water Boiling in Free Motion Conditions. 1963. Vol. 6, No 2. p. 3-7.
20. Mikheyev М. А., Mikheyeva I. M. Heat-Transfer Principles. 2nd edition stereotyped. М., 1977. 343 p.
21. Kutateladze S. S., Leontyev A. I. Heat-Mass Exchange and Friction in Turbulent Boundary Layer. М., 1972. 341 p.

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]]> 8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation https://journal.yuzhnoye.com/content_2019_1-en/annot_8_1_2019-en/ Thu, 25 May 2023 12:09:45 +0000 https://journal.yuzhnoye.com/?page_id=27713
2019, (1); 54-63 DOI: https://doi.org/10.33136/stma2019.01.054 Language: Russian Annotation: This paper describes the effective approach for the technology of the rocket airframe development testing, based on the method of numerical modelling, which enables the virtual experimental runs prior to the beginning of the development testing to check the performance of the standard airframes and predict issues of concern. Computational models, criteria and test procedures necessary for the analysis of the mechanical condition and prediction of the performance of the actual airframe of the warhead were developed. For the specified loading conditions during the ground operations with the warhead, the most dangerous computational cases are determined which have been implemented during the virtual tests. Key words: computer modelling , computational models , ground operations , mechanical condition , performance Bibliography: 1.
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8. Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Tonkonozhenko A. M.1, Kozharin V. Y.1, Martynenko G. Y.3, Chernobryvko M. V.2, Avramov K. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine2; National Technical University “Kharkiv Polytechnic Institute”, Kharkiv, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2019, (1); 54-63

DOI: https://doi.org/10.33136/stma2019.01.054

Language: Russian

Annotation: This paper describes the effective approach for the technology of the rocket airframe development testing, based on the method of numerical modelling, which enables the virtual experimental runs prior to the beginning of the development testing to check the performance of the standard airframes and predict issues of concern. The method is realized based on the computer models developed in the ANSYS Workbench environment. Based on the offered method the complex mechanical system, which attaches the cluster projectiles in the conditions of the temperature exposure and heat cycling, underwent the virtual tests. Computational models, criteria and test procedures necessary for the analysis of the mechanical condition and prediction of the performance of the actual airframe of the warhead were developed. Moreover, computational models consider all the design and technological features of the airframe: layout of the projectiles attachments, initial stress-strain state of the system after the tightening of the threaded connections, friction between the components of the system and their mutual displacement, temperature dependence of the physical and mechanical characteristics and ultimate stress of materials. For the specified loading conditions during the ground operations with the warhead, the most dangerous computational cases are determined which have been implemented during the virtual tests. Test results were used to conduct the static analysis of the mechanical condition, strength and conditions for performance of the actual structure of the attachment under the impact of the operating levels of temperature exposure and heat cycling. Results of the virtual tests confirm the performance of the projectiles attachment system and are introduced into production in the phase of engineering development.

Key words: computer modelling, computational models, ground operations, mechanical condition, performance

Bibliography:

1. Birger I. A., Iosilevich G. B. Rezbovye i flantsevye soedineniya. M.: Mashinostroenie, 1990. 368 p.
2. Kukhling Ch. Spravochnik po phisike. M.: Mir, 1985. 520 p.
3. Nikolskiy B. P., Rabinovich V. A. Spravochnil chimika. T. 6. L.: Chimiya, 1967. 1009 p.
4. Stali I splavy. Marochnik: Sprav. izd. / pod red. V. G. Sorokina, M. A. Gervasieva. M.: Intermet Engineering, 2001. 608 p.
5. Numerical simulation of missile warhead operation / G. Martynenko, M. Chernobryvko, K. Avramov, V. Martynenko, A. Tonkonozhenko, V. Kozharin, D. Klymenko / Advances in Engineering Software. 2018. Vol. 123. P. 93-103. https://doi.org/10.1016/j.advengsoft.2018.07.001

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]]> 18.1.2019 Designing of Servo Driver of Throttle Mechanisms and Fuel Flow Regulator of ILV Main Motor https://journal.yuzhnoye.com/content_2019_1-en/annot_18_1_2019-en/ Wed, 24 May 2023 16:00:39 +0000 https://journal.yuzhnoye.com/?page_id=27723
2019, (1); 122-131 DOI: https://doi.org/10.33136/stma2019.01.122 Language: Russian Annotation: The basic results of the design calculations and mathematical modelling of the control processes in the precision high-speed servo drive are presented, as well as results of experimental studies of the functional mock-up of this servo drive’s movable gears of the throttle and fuel flow regulator of the ILV main engine. Mathematical modelling of the control processes is conducted according to the computational model, varying the circuit and design parameters of the electric drive. Key words: control system , permanent-field synchronous motor , mathematical model , computational analysis Bibliography: 1. control system , permanent-field synchronous motor , mathematical model , computational analysis .
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18. Designing of Servo Driver of Throttle Mechanisms and Fuel Flow Regulator of ILV Main Motor

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Oslavsky S. Y., Fokin S. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 122-131

DOI: https://doi.org/10.33136/stma2019.01.122

Language: Russian

Annotation: The basic results of the design calculations and mathematical modelling of the control processes in the precision high-speed servo drive are presented, as well as results of experimental studies of the functional mock-up of this servo drive’s movable gears of the throttle and fuel flow regulator of the ILV main engine. Major task of the studies was theoretical and experimental verification of the required static and dynamic accuracy of the servo drive in the process of try-out of the command signals reception from the main engine’s controller. In the phase of development, theoretical study of the linearized servo drive with application of transformations and theorems of Laplace passages to the limit is conducted. Analytical dependences between servo drive circuit parametres, its elements and characteristics of the control signals are obtained. Instrument errors and servostatic elasticity of the servo drive are calculated. Calculation model including the basic nonlinearities of this servo drive is prepared. Mathematical modelling of the control processes is conducted according to the computational model, varying the circuit and design parameters of the electric drive. Results of the theoretical studies were taken as input data for the requirements specification document to develop the executive unit with the electromotor, reduction gear and output shaft position sensor, and the control box. Functional mockups of the executive unit, control box, as well as the computer-controlled technological test console were manufactured on the basis of the requirements specification documents. The required scope of the laboratory-development tests of the functional mock-up of the servo drive was conducted. Results of the conducted activities confirm the achievement of the required accuracies of the servo drive in the laboratory environment.

Key words: control system, permanent-field synchronous motor, mathematical model, computational analysis

Bibliography:
1. Programma «Mayak», raketa kosmicheskogo naznacheniya, marsheviy dvigatel’ pervoi stupeni: Techn. proekt. Dnepropetrovsk: GP KB «Yuzhnoye», 2015. 490 p.
2. Controller marshevogo dvigatelya pervoi stupeni RKN: Poyasnitelnaya zapiska. Dnepr: GP KB «Yuzhnoye», 2017. 108 p.
3. Marsheviy dvigatel pervoi stupeni RKN: Technicheskoe zadanie na razrabotku electromechanicheskogo privoda mechanizmov drosselya i regulyatora raschoda goryuchego. Dnepr: GP KB «Yuzhnoye», 2016. 68 p.
4. Basharin A. V., Novikov V. A., Sokolovskiy G. G. Upravlenie electroprivodami: Uch. posob. dlya VUZov. L.: Energoizdat, 1982. 392 p.
5. Makarov I. M., Menskiy B. M. Lineinye avtomaticheskie systemy. – 2-e izd., pererab. i dop. M.: Mashinostroenie, 1982. 504 p.
6. Otchet po rezultatam ispytania maketnogo obraztsa electromechanicheskogo privoda mechanizmov drosselya i regulyatora goruchego. Dnepr: GP KB «Yuzhnoye», 2018. 50 p.

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]]> 14.1.2019 Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins https://journal.yuzhnoye.com/content_2019_1-en/annot_14_1_2019-en/ Wed, 24 May 2023 16:00:23 +0000 https://journal.yuzhnoye.com/?page_id=27719
The methodology of estimation of the service life of material or structure is based on the generalization of great amount of Yuzhnoye SDO experimental data and theoretical research on the impact of various factors (properties of materials, loads, storage and operation conditions) on their service life on the ground of strength analysis. Developed methodological guidelines of the engineering estimate of the service life can be used as the computational basis for the service life of materials and structures in the phase of system design and updating of the assumed design solutions.
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14. Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Ushkin M. P.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 95-101

DOI: https://doi.org/10.33136/stma2019.01.096

Language: Russian

Annotation: Service life (resource) of the device (system, structure, material) is one of the major factors, which defines the reliable performance of the device or necessity of its replacement. The purpose of this paper is to develop the engineering methodology to estimate the service life of the device to support the well-founded design decision-making. The methodology of estimation of the service life of material or structure is based on the generalization of great amount of Yuzhnoye SDO experimental data and theoretical research on the impact of various factors (properties of materials, loads, storage and operation conditions) on their service life on the ground of strength analysis. At the same time, service life definition is based on the results of stress and deformation analyses and their comparison with strength properties of the applied material (tensile strength and deformation properties). Strength properties of the material should be reduced to test conditions in terms of temperature, pressure, rate of loading, degrees of material aging etc. Methodology provides the estimation of safety margins in all phases of storage and operation of the device, consideration of the impact of the active factors (mass, temperature, loading, process of material aging), performance of calculations for the chosen specific zones of the device. It is shown that the service life estimation is in general case a probabilistic observation because of the random combination of the influencing factors (strength properties, storage and operation conditions, loads). Analysis of experimental and computation data as applied to solid-propellant rocket engine shows that the most dangerous zones, which define the service life, are the fuel charge channel (deformations at launch), a fuel-body coupling zone (breakaway coupling stress) and a “lock” zone of the release collar (concentration of shear and breakaway stresses and deformations). Developed methodological guidelines of the engineering estimate of the service life can be used as the computational basis for the service life of materials and structures in the phase of system design and updating of the assumed design solutions.

Key words: stress, deformation, service life, aging, load

Bibliography:

1. Lyashevskiy A. V., Mironov Ye. A., Vedernikov M. V. Prognozirovanie srokov prigodnosti tverdykh raketnykh topliv metodom Roentgen-computrnoy tomografii// Aviatsionnaya i raketno-kosmichaskaya technika. №2. 2015. P. 118-123.
2. Schubert H., Menke K. Service Life Determination of Rocket Motors by Comprehensive Property Analysis of Propellant Grain / Athens, Greece, May, 1996, Simposium. №41 P. 1-10.
3. Hufferd W. L. Service Life Assessment for Space Launch Vehicles / Athens, Greece, May, 1996, Simposium. №46. P. 1-9.
4. Faulkner G. S., Tod D. Service Life Prediction Methodologies Aspects of the TTCP KTA-14 UK Programme / Athens, Greece, May, 1996, Simposium. – №24. P. 1-13.
5. Francis E. C. (England), Busswell H. J. Improvements in Rocket Motor Service Life Prediction / Athens, Greece, May, 1996, Simposium. №27. P. 1-13.
6. Collingwood G. A., Dixon M. D., Clark L. M., Becker E. B. Solid Rocket Motor Service Life Prediction Using Nonlinear Viscoelastic Analysis and Probabilistic Approach / Athens, Greece, May, 1996, Simposium. №29. P. 1-8.
7. Zharkov A. S., Anisimov I. I., Maryash V. I. Physiko-chimichaskie process v izdeliyakh iz vysokoenergetycheskykh kondensirovannykh materialov pri dlitelnoy ekspluatatsii/ Physicheskaya mezomechanika. №9/4. 2006. P. 93-106.
8. Gul’ V. Ye. Struktura i prochnost’ polymerov. M.: Chimia, 1971. P. 10-23, 189-209.
9. Pavlov P. A. Osnovy engeneernykh raschetov elementov machin na ustalostnuyu i dlitelnuyu prochnost’. L.: Mashinostroenie, 1988. P. 65-70.
10. Ushkin N. P. Sposoby proektnoy otsenki resursa RDTT i obespechaniya ego dlitelnoy ekspluatatsii/ Kosmicheskaya technika. Raketnoye vooruzhenie: Sb. nauch.- techn. st. 2016. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 110-116.

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]]> 17.1.2016 Modeling of Solid Rocket Motor Starting Process https://journal.yuzhnoye.com/content_2016_1/annot_17_1_2016-en/ Tue, 23 May 2023 13:13:20 +0000 https://journal.yuzhnoye.com/?page_id=27635
2016 (1); 105-109 Language: Russian Annotation: In this article was examined starting process of solid rockets motor (SRM) and built computational model of parameters SRM at the time of starting. A result from this model shows acceptable concordance with experimental data and calculations by standard methods Key words: Bibliography: Full text (PDF) ||
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17. Modeling of Solid Rocket Motor Starting Process

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Tikhaya M. V.1, Bucharsky V. L.2, Orekhov K. M.1

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2016 (1); 105-109

Language: Russian

Annotation: In this article was examined starting process of solid rockets motor (SRM) and built computational model of parameters SRM at the time of starting. A result from this model shows acceptable concordance with experimental data and calculations by standard methods

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17.1.2016 Modeling of Solid Rocket Motor Starting Process
17.1.2016 Modeling of Solid Rocket Motor Starting Process
17.1.2016 Modeling of Solid Rocket Motor Starting Process
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