Search Results for “Kushnir R. M.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 10 Mar 2026 09:53:19 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “Kushnir R. M.” – 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
1 , Kushnir R. 1   ORCID , Kushnir R. 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. 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. This paper demonstrates that the results of a tank strength analysis using a criterion of a maximum stress are closest to experimental data. Buraka, R.M. Kushnira. 4: Termomekhanika namahnechuvanykh elektroprovidnykh termochutlyvykh til. Kleiber M. V., Kushnir R. Missile armaments , ( V., Kushnir R. V., Kushnir R. V., Kushnir R. V., Kushnir R. V., Kushnir R.
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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

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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]]> 5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep https://journal.yuzhnoye.com/content_2020_1-en/annot_5_1_2020-en/ Wed, 13 Sep 2023 06:15:53 +0000 https://journal.yuzhnoye.com/?page_id=31026
Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep e-ISSN: 2617-5533 Authors: Hudramovych V. 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. L., Hudramovych V. Hudramovich V. Po problemam mekhaniki deform. Hudramovich V. Problemy nelineinogo deformirovaniia. Kushnir R. F., Hudramovich V. Hudramovich V. Hudramovich V. Mutual influence of openings on strength of shell-type structures under plastic deformation. Hudramovich V. Barmin I. Hudramovych V.
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5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

e-ISSN: 2617-5533

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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]]> 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
Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime e-ISSN: 2617-5533 Authors: Hudramovych V. http://www.yuzhnoe.com/presscenter/media/ photo/techique/launch-vehique. Kushnira. 3: Termopruzhnist’ termochutlyvykh til. 4: Termomechanica namagnychuvannykh electroprovodnykh nermochutlyvykh til. Hudramovich V. Hudramovich V. Hudramovich V. Hudramovich V. Hudramovich V. Lvyv: Prostir-M, 2017. Hudramovich, V. Karmishin A. Lvyv: Prostir-M, 2016. Barmina. M.: Mir, 1973. 2019, (1) (March): 28—37. Hudramovych V. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime Автори: Hudramovych V.
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5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

e-ISSN: 2617-5533

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

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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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]]> 9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software https://journal.yuzhnoye.com/content_2023_1-en/annot_9_1_2023-en/ Fri, 12 May 2023 16:11:14 +0000 https://test8.yuzhnoye.com/?page_id=26993
, Kushnir B. Furthermore, the ability of modern technologies to produce different arms systems, which are capable of carrying out same class tasks, considerably increases the risk of making not the best decisions. The problems related to this have been shown. In particular, searching for the compromise between simplicity of the mathematical model and its adequacy to the research object is among these problems. The first is implemented through modeling of the combat operations. G., Kushnir B. S., Kushnir B. Raschetnye materialy dlya podgotovki i vydachi iskhodnykh dannykh na razrabotku uzlov marshevykh dvigatelnykh ustanovok na tverdom toplive. H., Kushnir B. Missile armaments , ( Missile armaments , no. H., Kushnir B. Missile armaments, vol. H., Kushnir B. H., Kushnir B. H., Kushnir B. H., Kushnir B.
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9. Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software

e-ISSN: 2617-5533

Authors:

Yenotov V. H., Kushnir B. I., Pustovharova O. V., Chubarov A. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 77-87

DOI: https://doi.org/10.33136/stma2023.01.077

Language: Ukrainian

Annotation: Substantiation of the research tools has been performed as a part of methodology development for the air and missile defense system. The problem under consideration is very complex due to the multifactorial nature of the research object, its qualitative variety and manifold structure, incomplete definition of the problem statement. Furthermore, the ability of modern technologies to produce different arms systems, which are capable of carrying out same class tasks, considerably increases the risk of making not the best decisions. Based on this, as well as taking into account the sharp increase in the cost of weaponry, the considered problem is classified as an optimization one that should be solved through the theory of operations research. In this theory, such task is viewed as a mathematical problem, and mathematical simulation is the basic method of research. The main types of mathematical models, their areas of application have been considered as a part of the analysis. The classification of mathematical models has been indicated according to the scale of reproduced operations, purpose, and goal orientation. Quantitative and qualitative correlation of forces has been accepted as the efficiency criterion, which determines a goal orientation of the model. The problems related to this have been shown. In particular, searching for the compromise between simplicity of the mathematical model and its adequacy to the research object is among these problems. Two of the basic approaches to principles of the military operation model construction and its assessment have been considered. The first is implemented through modeling of the combat operations. The second approach is based on the assumption that different armament types can be compared based on their contribution to the outcome of the operation, and on the possibility to assign «a weighting coefficient» named as a combat potential to each of these types. The modern level of problem solving related to this method has been shown. The reasonability of its application in the considered task, including the definition of forces correlation of the opposing parties, has been substantiated. The basic regulations of the construction concept of the required mathematical model and tools for its research have been formulated based on the analysis results: the assigned problem should be solved by analytical methods through the theory of operations research; the analytical model is the most acceptable conception of the analyzed level of the military operation; the synthesis of the model should be based on the idea of a combat potential. At the same time, it should be taken into account that the known approach to the definition of forces correlation, which uses the combat potential method, has a number of essential limitations, including the methodological ones. Therefore, within the bounds of further research, this approach requires the development both in terms of improving the reliability of the single assessment and in terms of giving the system qualities to the synthesized mathematical model.

Key words: multifunctional system, mathematical model, military unit, combat potential, correlation of forces, defensive sufficiency

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