Search Results for “fi nite element method” – Collected book of scientific-technical articles

1.2.2025 Methods for structural strength investigations of rocketry.

manager — Tue, 27 Jan 2026 01:13:55 +0000

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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6.1.2025 Studying the landing of the reusable first stage of the Cyclone-5 space launch vehicle on a maritime landing platform-duplicate-1

manager — Wed, 27 Aug 2025 13:43:20 +0000

6. Mining on the Moon

ISSN: 2617-5525

e-ISSN: 2617-5533

Автори: Gusarova I. O., Kozis K. V, Osinovyy G. G.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2025 (1); 45-51

DOI: https://doi.org/10.33136/stma2025.01.045

Language: English

Annotation: Modern research into technologies for extracting mineral resources on the Moon has revealed some harsh limitations related to dependence on Earth’s resources and high technological requirements. While the chemical and carbothermal reduction of lunar regolith is theoretically possible, it requires a constant supply of reducing agents such as hydrogen or carbon from Earth. This signifi cantly increases mission costs and complicates logistics, making such methods unsuitable for large-scale applications. Pyrolysis, which involves heating regolith to extremely high temperatures, is also not an optimal solution due to the need for complex and energy-intensive equipment that exceeds the capabilities of current space technologies. Electrolysis using molten fl uoride salts or calcium chloride (CaCl2 ) has been proposed as an alternative, but its effi ciency is limited by the need to deliver fl uxes from Earth. This reduces the autonomy of the process and makes it less economically viable in the long term. In light of these limitations, the most promising technology appears to be the direct electrolysis of molten regolith, which stands out for its simplicity and independence from terrestrial materials. This method involves melting local raw materials, followed by electrolytic separation into useable components such as oxygen, metal alloys, and other materials. However, the key challenge to implementing this technology is the development of refractory conductive materials for anodes that can withstand the extreme conditions of high temperatures and aggressive oxygen environments. Existing materials degrade rapidly under these factors, leading to reduced effi ciency and increased maintenance costs. Additionally, reliable protective coatings for equipment must be developed to prevent corrosion and mechanical wear. Overcoming these technical challenges would enable the creation of an autonomous lunar resource extraction system, which is critical for future lunar bases and further space exploration. Such a system could provide astronauts with oxygen, water, and construction materials without constant supplies from Earth, signifi cantly reducing the cost of space missions. Thus, despite existing technological challenges, direct electrolysis remains the most viable option for the industrial use of local lunar resources. Further research should focus on optimizing materials and application methods, as well as on developing energy-effi cient solutions to ensure the stability and economic feasibility of lunar mining. This will open new possibilities for a sustained human presence on the Moon and will be a signifi cant step in deep space exploration.

Key words: Electrochemical reduction of melts, inert anodes, electrolysis, pyrolysis

Bibliography:

1. NEEP602 Course Notes (Fall 1996) Resources from Space. URL: https://fti.neep.wisc.edu/fti.neep.wisc.edu/neep602/lecture12.html.

2. Lunarpedia. Ilmenite Reduction. URL: https://lunarpedia.org/w/Ilmenite_Reduction.

3. S. J. Barber et al. ProSPA: Analysis of Lunar Polar Volatiles and ISRU Demonstration on the Moon. 49th Lunar and Planetary Science Conference 2018 (LPI Contrib. No.
2083). URL: https://www.cosmos.esa.int/documents/1568476/1766000/RD5_2018_LPSC_ PROSPECT_ProSPA_Poster_Abstract2172.pdf

4. Oxygen on the Moon. Oxygen production in the Moon extended summary. URL: https://www.ou.edu/class/che-design/a-design/projects-2004/Oxygen-Production-in-the-Moon-
Extended-Summary.pdf.

5. The Moon’s top layer alone has enough oxygen to sustain 8 billion people for 100,000 years. URL: https://theconversation-com./the-moons-top-layer-alone-has-enough-
oxygen-to-sustain-8-billion-people-for-100-000-years.

6. From lunar regolith to oxygen and structural materials: an integrated conceptual design. URL: https://link.springer.com/article/10.1007/s12567-022-00465-w.

7. Proving the viability of an electrochemical process for the simultaneous extraction of oxygen and production of metal alloys from lunar regolith. URL:
https://pure.hw.ac.uk/ws/portalfiles/portal. Lomax, BA, Conti, M, Khan, N, Bennett, NS, Ganin, AY & Symes, MD 2019. Proving the viability of an electrochemical process
for the simultaneous extraction of oxygen and production of metal alloys from lunar regolith, Planetary and Space Science. https://doi.org/10.1016/j.pss.2019.104748.

8. L. Glaze, Moon’s South Pole in NASA’s Landing Sites, NASA. (2019). URL: https://www.nasa.gov/feature/moon-s-south-pole-in-nasa-s-landing-sites.

9. Feasibility Analysis of Liquefying Oxygen Generated from Water Electrolysis Units on Lunar Surface. URL: https://ntrs.nasa.gov/citations/20100020908, Feasibility
Analysis of Liquefying Oxygen Generated from Water Electrolysis Units on Lunar Surface.

10. Moon oxygen startup stumbles on ‘green’ iron production-method. URL: https://www.israelhayom.com/2022/07/17/moon-oxygen-startup-stumbles-on-green-iron-production-
method.

11. Eric Berger. Machine to melt Moon rocks and derive metals may launch in 2024. URL: https://arstechnica.com/science/2022/01/machine-to-melt-moon-rocks-and-derive-
metals-may-launch-in-2024.

12. Hydrogen-oxygen proton-exchange membrane fuel cells and electrolyzers. URL: https://www.science.gov/topicpages/e/electrolyzer+component+development.

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Виктория Лемех — Tue, 09 Jan 2024 13:29:00 +0000

Документи щодо організації освітньої діяльності

Документи щодо організації освітньої діяльності

• Концепція освітньої діяльності Державного підприємства “Конструкторське бюро “Південне” імені М.К. Янгеля”

• Положення про порядок здійснення освітньої діяльності на третьому етапі вищої освіти здобуття ступеня доктора філософії

• Договір про співробітництво між ДП “КБ “Південне” та Дніпровським національним університетом № 5-18 від 17.07.2018

• Положення про наукового керівника здобувача наукового ступеня доктора філософії в аспірантурі ДП “КБ “Південне” ім. М.К. Янгеля”

• Положення про підвищення кваліфікації (стажування) науково-педагогічних працівників

Освітньо-наукова програма

Освітньо-наукова програма “Авіаційна та ракетно-космічна техніка”

• ОНП

⇒ 2017
⇒ 2022

• Рецензії-відгуки стейкхолдерів

ДП «Івченко-Прогрес»

Дніпровського національного університу

Інститут технічної механіки

Національного центру аерокосмічної освіти молоді

ПРО НАС

1. Ліцензія на підготовку докторів філософії

2. Гарант, група забезпечення ОНП, група забезпечення ОП

⇒ 2021
⇒ 2022

3. Сертифікати викладачів:
✓ Зєвако Василь Сергійович;
✓ Кирпита Тамара Володимирівна;
✓ Козак Леонід Романович;
✓ Логвиненко Анатолій Іванович;
✓ Потапович Лариса Петрівна;
✓ Трубін Анатолій Володимирович;
✓ Фролов Віктор Петрович;
✓ Хорошилов Віктор Сергійович.

4. Положення про аспірантуру

5. Колектив аспірантури

3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

manager — Fri, 29 Sep 2023 18:22:49 +0000

3. Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Degtiarov М. O.¹, Avramov K. V.²

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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14.1.2020 On the problem of optimum control

Вацлав Самусевич — Wed, 13 Sep 2023 11:02:31 +0000

14. On the problem of optimum control

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Zavialov P. P., Sidoruk V. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 133-136

DOI: https://doi.org/10.33136/stma2020.01.133

Language: Russian

Annotation: The use of Langrangian multipliers at solution of optimal control problems in linear statement with qua dratic quality criterion leads to the necessity of solving boundary value problem with conditions for multipliers at the right end of control interval. Solution of the obtained equations for the purpose of regulation synthesis in forward time in this case does not produce stabilizing effect, as a rule. For regulation synthesis, the met hod is widely used of analytical construction of optimal regulator based on stabilizing matrix, which is obtained by solution of algebraic Riccati equation. However, in this case, there are some difficulties ‒ the necessity of calculating the stabilizing matrix, impossibility of calculating this matrix in non-stationary problem. The article proposes the regulation synthesis method by way of solving boundary value problem on regulation cycle i nterval. For this purpose, the differential equations for state parameters and Langrangian multipliers are expressed in the form of finite-difference linear relations. Taking into account that the state parameters and Langrangian multipliers are equal to zero at the end of cycle, the Langrangian multipliers at the beginning of cycle are determined by known values of state parameters for the same moment through solving the above linear system. The obtained values form the regulation law. In consequence of small duration of regulation cycle, an amplifying coefficient is introduced in the regulation law. Its value is determined based on results of preliminary modeling. Efficiency of the proposed method was verified by the example of adopted dynamic system, including non-stationary. The amplifying coefficient is fairly simply selected by the type of stabilization process. The proposed method may be used in the control systems of rockets of various purpose for motion parameters regulation.

Key words: optimal control, regulation law, Langrangian multiplier, regulation cycle interval, amplifying coefficient

Bibliography:

1. Braison A., Kho Yu-Shi. Prikladnaia teoriia optimalnogo upravleniia. М., 1972.

2. Larin V. B. O stabiliziruiushchikh i antistabiliziruiushchikh resheniiakh algebraicheskikh uravnenii Rikkati. Problemy upravleniia i informatiki. 1996. №1-2.

3. Aleksandrov А. G. Optimalnye i additivnye sistemy. М., 1989.

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16.2.2016 Method of Coefficient for Optimization and Analysis of Operating State of Fine Filter Cases

Виктория Лемех — Tue, 06 Jun 2023 12:05:36 +0000

16. Method of Coefficient for Optimization and Analysis of Operating State of Fine Filter Cases

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Satokin V. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (2); 98-101

Language: Russian

Annotation: The problem of numerical simulation of operating condition of Thermostating System fine filter casings is considered. A method of coefficient, allowing for optimal functioning, is discovered and proven. Investigation was conducted in the finite element analysis package ANSYS.

Key words:

Bibliography:

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13.2.2019 Study of the stress and strain state of the multilayer bellows

manager — Mon, 15 May 2023 15:46:07 +0000

13. Study of the stress and strain state of the multilayer bellows

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Vasilieva T. M., Strunin K. A., Onofriienko V. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 96-102

DOI: https://doi.org/10.33136/stma2019.02.096

Language: Russian

Annotation: Strength calculation example of the specific design bellows is taken to consider one of the possible approaches to the numerical simulation of the stress and strain state of the multilayer bellows. Proposed approach is based on the use of axial symmetry of the structure for transition from 3D calculation model to 2D one. Calculations take place in the elastoplastic setup, using the software package of the finite elements method. As an example of the proposed approach static and fatigue strength of the three-layer steel bellows of the Cyclone-4M fuel supply line are calculated. Calculation of the static strength of the bellows, loaded with internal pressure, showed that layer stresses achieve yield strength, at the same time preserving the bearing capacity of the structure. Results of the simulated change in the stress and strain state of the bellows per one cycle of the variable reloading were taken to find the amplitude of the plastic deformations in the most loaded area of the bellows, which allowed estimation of its fatigue strength in the conditions of lowcycle loading. Advantage of the proposed approach to the multilayer bellows strength evaluation is that it does not require large volumes of RAM and time to do the calculations.

Key words: computer simulation, finite element method, calculation model, strength

Bibliography:

1. GOST 21744-83. Silfony mnogosloynye metallicheskie. Obschie technicheskie uslovia. 72 s.

2. Prochnost’, ustoychivost’, kolebaniya: spravochnil; v 3-kh t. / pod red. I. A. Birgera, Ya. G. Panovko. M., 1968. T. 2. 462 s.

3. Grabin B. V., Davydov O. I., Zhikharev V. I. i dr. Osnovy konstruirovaniya raket-nositeley kosmicheskykh apparatov: uchebnik dlya studentov vuzov / pod red. V. P. Mishina, V. K. Karraska. M., 1991. 416 s.

4. Silfony. Raschet i proektirovanie / pod red. L. Y. Andreevoy. M., 1975. 156 s.

5. Issledovanie vliyaniya tekhnologicheskykh operatsiy na kachestvo izgotovleniya silfonov iz lenty staly marki DIN 1.4541 EN 1099-2 pri razlichnykh temperaturno-silovykh vozdeistviyakh i vibratsiyakh v processe izgotovleniya i ispytaniy: techn. otchet № 3 М-13 / PO YMZ im. A. M. Makarova». Dnepropetrovsk. 2013. 13 s.

6. Pisarenko G. S., Yakovlev A. P., Matveev V. V. Spravochnik po soprotivleniyu materialov / otv. red. Pisarenko G. S. 2-e izd., pererab. i dop. Kiev. 1988. 736 s.

7. Gusenkov A. P., Moskvitin G. M., Khoroshilov V. N. Malotsiklovaya prochnost’ obolochechnykh konstruktsiy. M., 1989. 254 s.

8. Kogaev V. P., Makhutov N. A., Gusenkov A. P. Raschety detaley mashin na prochnost’ i dolgovechnost’: spravochnik. M., 1985. 224 s.

9. DSTU EN 10088-2:2010. Stali nerzhavki. Ch. 2. List i strichka z koroziynotryvkykh staley zagalnoi pryznachenosti. Technichni umovy postachannya. 42 s.

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4.2.2019 Numerical simulation of behavior of elastic structures with local stiffening elementse

manager — Mon, 15 May 2023 15:45:37 +0000

4. Numerical simulation of behavior of elastic structures with local stiffening elements

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Hudramovych V. S.¹, Hart Ye. L.³, Strunin K. A.²

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, (2); 25-34

DOI: https://doi.org/10.33136/stma2019.02.025

Language: Russian

Annotation: Availability of different inclusions, stiffenings, discontinuities (holes, voids and flaws) are the factors that cause structural irregularity and are typical for structural elements and buildings from various current technology areas, in particular aerospace technology. They significantly influence the deformation processes and result in stress concentration, which can cause local damages or malconformations and as a result lead to impossibility to further use the structure. Materials used are also heterogeneous in its structure. Inclusions can simulate thin stiffening elements, straps, welded or glue joints. It is necessary to detect the thin inclusions when phase transformations of materials are studied, for example, when martensite structures are formed. Study of the various bodies with inclusions is very important in the powder technology, ceramics, etc., where powder, previously compressed under high pressure, is sintered at high temperatures. Use of surface hardening that increases working efficiency of the structural elements is prospective in many engineering sectors. It is important to develop discrete hardening, implemented through manufacturing schemes of particular type. When discrete hardenings impact on the structural elements mode of deformation is simulated, they can also be considered as inclusions of specific structure. Inclusions can also simulate banding of the ferritic-pearlitic structure in the microstructure, related to the complex preloading under material plastic forming. It is advisable to use numerical methods for studies that are universal and suitable for objects of various shapes, sizes and types of loading. Main numerical methods are finite difference method, boundary element method, variation grid-based method, finite element method, method of local variations. This article features ANSYS – based computer simulation of the aerospace structural element behavior – a rectangular plate with two extended elastic inclusions of different rigidity, simulating elastic heterogeneities of structures and materials.

Key words: finite-element method, strength, inclusions, computer simulation

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7. Hart E. L., Hudramovich V. S. Proektsionno-iteratsionnaya modifikatsia metoda lokalnykh variatsiy dlya zadach s kvadratychnym funktsionalom. Prikl. Matematika I mekhanika. 2016. T. 80, № 2. S. 218–230. https://doi.org/10.1016/j.jappmathmech.2016.06.005
8. Hudramovich V. S. Osobennosti neuprugogo povedeniya neodnorodnykh obolochechnykh elementov konstruktsiy. Aktualnye problem mekhaniki: monografia/ za red. M. V. Polyakova. Dnipro, 2018. S. 195–207.
9. Hudramovich V. S., Hart E. L. Konechnoelementniy analiz processa rasseyanogo razrusheniya ploskodeformiruemykh uprugoplastichnykh sred s lokalnymi contsetratami napryazheniy. Uprugost’ I neuprugost’: Materialy Mezhdunarod. nauchn. symp. po problemam mekhaniki deformiruemykh tel, posvyaschennogo 105-letiyu so dnya rozhdeniya A. A. Ilyushina (Moskow, 2016 ). M., 2016. S. 158–161.
10. Hudramovich V. S., Hart E. L., Strunin K. A. Modelirovanie processa deformirovaniya plastiny s uprugimi protyazhonnymi vklyucheniyami na osnove metoda konechnykh elementov. Tekhn. mechanika. 2014. № 2. S. 12–24.
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Finite element method in determining the destructive load on the perforated shell under short-term forces

Kirill Degtyarev, Vasyl Gnitko, А. М. Тонконоженко (2020)

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