Search Results for “finite-element model” – Collected book of scientific-technical articles

11.1.2020 Some results of strength calculations relying on analytical and FEM approaches. Trends of using contemporary machine learning strategies

Вацлав Самусевич — Wed, 13 Sep 2023 10:51:08 +0000

11. Some results of strength calculations relying on analytical and FEM approaches. Trends of using contemporary machine learning strategies

Authors:

Gryshchak V. Z.

Organization:

Zaporizhzhia National University, Zaporizhzhia, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 107-113

DOI: https://doi.org/10.33136/stma2020.01.107

Language: Russian

Annotation: This article analyzes the results of studies, which are based on numerical methods of analysis, of the stress-strain state of thin-walled shell structures. This article also discusses analytical solutions that apply asymptotic approaches and a method of initial parameters in a matrix form for solving a problem of equal stability of reinforced compartments of combined shell systems of the rocket and space technology within the scope of the research being carried out jointly by teams of Yuzhnoye State Design Office and Zaporizhzhya National University. The primary attention is paid to the use of FEM-based direct numerical methods and the research results for which analytical methods can be useful for making a preliminary assessment of the bearing capacity of load-bearing structures, and in some cases for their rational design. This article does not contrast numerical and analytical approaches but about the possibility of using them effectively. The article talks about possible ways of using the up-to-date technique of machine learning (Machine Learning Technology) in the calculation and experimental methods for determining the characteristics of the rocket and space technology.

Key words: numerical and analytical methods, stress-strain state, rocket structures, shell system, reinforcing load-bearing elements, local and general stability, machine learning technology

Bibliography:

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3. Akimov D. V., Gristchak V. Z., Gomenjuk S. I., Larionov I. F., Klimenko D. V., Sirenko V. N. Finite-element analysis and experimental investigation on the strength of a three-layered honeycomb sandwich structure of spacecraft adapter module. Strength of Materials. 2016. № 3. P. 52–57. https://doi.org/10.1007/s11223-016-9775-y

4. Akimov D. V., Larionov I. F., Klimenko D. V., Gristchak V. Z., Gomenjuk S. I. Matematicheskoe modelirovanie i issledovanie napriazhenno-deformirovannogo sostoianiia otsekov raket kosmicheskogo naznacheniia. Kosmicheskaya tekhnika. Raketnoe vooruzhenie: sb. nauch.-tekhn. st. GP «KB «Yuzhnoye». Dnipro, 2019. Vyp. 1. S. 21–27. https://doi.org/10.33136/stma2019.01.021

5. Yarevskii Ye. А. Teoreticheskie osnovy metodov kompiuternogo modelirovaniia: ucheb.-metod. posobie. Sankt-Peterburg, 2010. 83 S.

6. Klovanich S. F. Metod konechnykh elementov v nelineinykh zadachakh inzhenernoi mekhaniki. Zaporozhie, 2009. 394 S.

7. Akimov D. V., Gristchak V. Z., Larionov I. F., Gomenjuk S. I., Klimenko D. V., Choporov S. V., Grebenyk S. N. Matematicheskoe obespechenie analiza prochnosti silovykh elementov raketno-kosmicheskoi techniki. Problemy obchysliuvalnoi mekhaniky i mitsnosti konstruktsii: zb. nayk. prats. 2017. Vyp. 26. S. 5–21.

8. Akimov D. V., Gristchak V. Z., Gomenjuk S. I., Larionov I. F., Klimenko D. V., Sirenko V. N. Eksperimentalnoe issledovanie deformirovannogo sostoianiia i prochnosti mezhstupenchatogo otseka raketonositelia pri staticheskom vneshnem nagruzhenii. Novi materialy i technolohii v metalurhii ta mashynobuduvanni. 2016. №1. S. 82–89.

9. Akimov D. V., Gristchak V. Z., Grebenyk S. N., Gomenjuk S. I. Sravnitelnyi analiz metodik rascheta napriazhenno-deformirovannogo sostoianiia elementov konstruktsii raketonositelia. Novi materialy i technolohii v metalurhii ta mashynobuduvanni. 2016. № 2. S. 116–120.

10. Gristchak V. Z., Gomeniuk S. I., Grebeniuk S. N., Larionov I. F., Degtiarenko P. G., Akimov D. V. An Investigation of a Spacecraft’s Propellant Tanks Shells Bearing Strength. Aviation in XXI-st Century. Safety in Aviation and Space Technologies: Proccedings the Sixth world congress. Kiev, 2014. Vol. 1. Р. 1.14.49–1.14.51.

11. Gristchak V. Z., Manievich А. I. Vliianiie zhestkosti shpangoutov na izgib iz ploskosti na ustoichivost podkreplennoi tsilindricheskoi obolochki. Gidroaeromechanika i teoriia uprugosti. 1972. Vyp. 14. S. 121–130.

12. Gristchak V. Z., Diachenko N. M. Opredelenie oblastei ustoichivosti konicheskoi obolochki pri kombinirovanom nagruzhenii na baze gibridnogo asimptoticheskogo podkhoda. Visn. Zaporiz’koho nats. un-tu. Fiz.-mat. nauky. 2017. №2. S. 32–46. URL: http:// nbuv.gov.ua/UJRN/Vznu_mat_2017_2_6.

13. Dehtiarenko P. H., Gristchak V. Z., Gristchak D. D., Diachenko N. M. K probleme ravnoustojchivosti podkreplenoi obolochechnoi konstruktsii pri kombinirovannom nagruzhenii. Kosmicheskaia nauka I technologiia. 2019. Т. 25, № 6(121). S. 3–14.

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16. Choporova О. V., Choporov S. V., Lysniak А. О. Vykorystannia mashynnoho navchannia dlia prohnozuvannia napruzheno-deformovannoho stanu kvadratnoi plastyny. Matematychne modeliuvannia fizychnykh I tekhnolohichnykh system. Visnyk KhNTU. 2019. № 2(69). S. 192–201.

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8.2.2016 Development and Validation of Program Module for Construction of Virtual Models of Real Structures in ANSYS System

Виктория Лемех — Tue, 06 Jun 2023 11:55:36 +0000

8. Development and Validation of Program Module for Construction of Virtual Models of Real Structures in ANSYS System

Authors:

Satokin V. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (2); 57-59

Language: Russian

Annotation: Software module is developed for virtual source construction based on 3D scanner data for finite-element analysis complex ANSYS.

Key words:

Bibliography:

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4.1.2019 Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays

manager — Thu, 25 May 2023 12:09:18 +0000

4. Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays

Authors:

Akimov D. V.¹, Larionov I. F.¹, Klimenko D. V.¹, Gryshchak V. Z.², Gomenyuk S. I.²

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2019, (1); 21-27

DOI: https://doi.org/10.33136/stma2019.01.021

Language: Russian

Annotation: This paper presents the overview and features of the stress-strain state analysis of the multilayer shell structures widely used in the design of the missile compartments. As a result of analysis of the current situation with the stress-strain state studies of the complex configuration shell structures and mathematical support of the load-bearing capacity calculation of the aerospace structures, the following actual research trends can be singled out: 1) improvement of the methods of analytical estimation of the thin-walled structures’ strength and resistance; 2) improvement of the numerical methods of composite materials mechanical properties analysis; 3) development or application of the existing software packages and ADE-systems, automatizing stress-strain state analysis with visualization of the processes under study. One of the most important steps of the third research trend is development of the initial data input media (setting the model parameters) and presentation of analysis results with account of the user interface visualization. The description of the mathematical simulation and experimental studies of the stress-strain state of the interstage bay made of carbon fiber sandwich structure is presented and short description of the structure condition after the tests is provided. Based on the analysis it can be concluded that development of the geometric simulation methods, taking into account the manufacturing deviations, is an independent problem from the point of view of practical applications in the aerospace technology.

Key words: sandwich structure, interstage bay, finite-element model, manufacturing deviations, test loads

Bibliography:

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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

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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