Search Results for “strength testing” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Mon, 16 Mar 2026 18:22:25 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “strength testing” – 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
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. 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
Key words: Strength parameters; aircraft , space and rocket technologies; design parameters; mathematical simulation; fuel tank; separation diafragm; autonomous bench testing; critical pressure Bibliography: 1. Strength parameters; aircraft , space and rocket technologies; design parameters; mathematical simulation; fuel tank; separation diafragm; autonomous bench testing; critical pressure .
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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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]]> 6.1.2024 New methods of load-carrying capacity prediction for the ultimately compressed frame structures https://journal.yuzhnoye.com/content_2024_1-en/annot_6_1_2024-en/ Mon, 17 Jun 2024 07:56:18 +0000 https://journal.yuzhnoye.com/?page_id=34992
To perform static strength testing, the rocket and space companies use costly compartments of as-built dimension.
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6. New methods of load-carrying capacity prediction for the ultimately compressed frame structures

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Muliar Yu. M.1, Fedorov V. M.1, Triasuchov L. М.2, Kalakutskyi R. G.1

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine,1; Kharkiv Aviation Institute, Kharkiv, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2024, (1); 51-60

DOI: https://doi.org/10.33136/stma2024.01.051

Language: English

Annotation: Amid acute problems that arise in the field of rocket and space technology, mechanical engineering, and other fields and require a workable engineering solution, the problem of prediction and prevention of the unpredicted collapse of the structural members of the structures subjected to loading is considered. Prediction of the load-carrying capacity and residual life of the space frames during the long-term operation is based on the analysis of the stress and strain state, using readings from the strain and displacement pickups installed in the most loaded zones. In this case the yield strength of the structural material or the fatigue strength of the material may be considered as the criterion of the maximum load. At the same time the loss of stability of the compressed structural members used in the load-carrying thin-walled structures are among the potentially dangerous failure modes. In these cases such failure occurs unexpectedly without any visible signs of change in the initial geometry. Application of the adequate diagnostic techniques and methods of prediction of the maximum loads under compression conditions will make it possible to avoid the structural failures. In this case an assembly under test may be used for other purposes. To perform static strength testing, the rocket and space companies use costly compartments of as-built dimension. Therefore, keeping compartments safe solves an important problem of saving financial costs for hardware production. Nowadays this problem is particularly acute when ground testing the new technology prototypes.

Key words: space frames, load-carrying members, stress and strain state, loss of stability, prediction of the structural failure.

Bibliography:
  1. Prochnost raketnyh konstruktsyi. Ucheb. posobie pod redaktsiyei V.I. Mossakovskogo. M.: Vyssh. shk., 1990. S. 359 (in Russian).
  2. Truesdell C. A first course in rational continuum mechanics. The Johns Hopkins University, Baltimore, Maryland, 1972. Russian translation was published by Mir, M., 1975. P. 592.
  3. Rabotnov Yu. Mehanika deformiruyemogo tverdogo tela.: Nauka, 1979. S. 744.
  4. Bolotin V. Nekonservativnyie zadachi teoriyi uprugoy ustoychivosti. Phyzmatgiz, M., 1961. S. 339.
  5. Feodosyev V. Izbrannyie zadachi i voprosy po soprotivleniyu materialov. Nauka. , 1973. S. 400.
  6. Muliar Yu. M., Fedorov V.M., Triasuchev L.M. O vliyanii nachalnyh nesovershenstv na poteryu ustoychivosti sterzhney v usloviyah osevogo szhatiya. Kosmicheskaya tehnicka. Raketnoye vooruzheniye: Sb. nauch.-tehn. st. 2017. Vyp. 1 (113). S. 48-58. https://doi.org/10.15193/zntj/2017/113/210
  7. Volmir A. Ustoychivost deformiruyemyh sistem. M., 1967. S. 984.
  8. Muliar Yu. M. K voprosy ob ustoichivosty szhatogo sterzhnya. Tekhnicheskaya mekhanika. Dnepropetrovsk: ITM. 2000. No S. 51.
  9. Muliar Yu. M., Perlik V.I. O matematicheskom modelnom predstavlenii informatsionnogo polia v nagruzhennoy deformiruyemoy sisteme. Informatsionnyie i telekommunikatsionnyie tehnologii. M.: Mezhdunar. akad. nauk informatizatsii, informatsionnyh protsessov i tehnologiy. 2012. No 15. S. 61.
  10. Koniuhov S. N., Muliar Yu. M., Privarnikov Yu. K. Issledovaniye vliyaniya malyh vozmuschayuschih vozdeystviy na ustoychivost obolochki. Mehanika. 1996. 32,  No 9. S. 50-65.

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]]> 20.2.2018 The Use of Special Devices during Launch Pad Development Testing https://journal.yuzhnoye.com/content_2018_2-en/annot_20_2_2018-en/ Thu, 07 Sep 2023 12:27:24 +0000 https://journal.yuzhnoye.com/?page_id=30805
The Use of Special Devices during Launch Pad Development Testing ISSN: 2617-5525 e-ISSN: 2617-5533 Authors: Fedenko B. 2018 (2); 173-177 DOI: https://doi.org/10.33136/stma2018.02.173 Language: Russian Annotation: One of the tasks of the development tests conducted on a launch pad is verification of its strength properties. This device enables to conduct static nondestructive tests on the launch pad in order to check its strength after manufacturing and during the whole operating period. Advantages of the pad loading device include low materials consumption, low cost in comparison with composite weights (with large load values), provision of the required modes for applying and removing the test load, controlled separate loading of each support of the launch pad, high mobility, short duration of testing, possibility of using launch pads of other rocket complexes with lower or equal test load values for testing.
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20. The Use of Special Devices during Launch Pad Development Testing

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Fedenko B. R., Onischenko S. M., Yerofeyev S. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 173-177

DOI: https://doi.org/10.33136/stma2018.02.173

Language: Russian

Annotation: One of the tasks of the development tests conducted on a launch pad is verification of its strength properties. The tests are carried out after the launch pad was manufactured and assembled on-site as well as during the whole operating period (if necessary). Load mode was chosen in consideration of cost and possibility of providing the required loading conditions. Two modes of creating the required test load were examined: usage of weights with corresponding mass (load simulators) or special devises (which have smaller mass as compared with load simulators). The descriptions, basic characteristics, advantages and disadvantages of composite and bulk weights and pad loading device are given. This article studies the pad loading device under development. This device enables to conduct static nondestructive tests on the launch pad in order to check its strength after manufacturing and during the whole operating period. The device consists of the load-bearing frame, hydraulic system, locks, control system and measurement system. Advantages of the pad loading device include low materials consumption, low cost in comparison with composite weights (with large load values), provision of the required modes for applying and removing the test load, controlled separate loading of each support of the launch pad, high mobility, short duration of testing, possibility of using launch pads of other rocket complexes with lower or equal test load values for testing. Therefore, the pad loading device enables to achieve the required test load values while having considerably smaller dimensions and mass as compared with composite weights and bigger functional possibilities as compared with bulk weights. Small overall dimensions and operability reduce the number of needed personnel and equipment.

Key words: weight for testing, test load, loading device

Bibliography:
1. ISO 14625:2007. Space systems. Ground support equipment for use at launch, landing or retrieval sites. General requirement. Brought in 01.11.2007. 32 p.
2. Launch Vehicle Mass Dummy: Patent RU2491211 RF: MPK B64G 5/00, B64G 7/00, F42B 15/00 / Dneprotyazhmash. Published 27.08.2013. 12 p.
3. Method of Poles Static Testing and Poles Static Test Device: Patent RU2173747: RF E02D 33/00 / NPSF Fundamentspetstroy. Published 20.09.2001. 10 p.
4. ISO 16290:2013. Space systems. Definition of the Technology Readiness Levels (TRLs) and their criteria of assessment. Brought in 14.10.2013. 20 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. 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.
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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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]]> 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
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.
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5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

ISSN: 2617-5525

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

Bibliography:

1. Vidy startovykh kompleksov: GP KB «Yuzhnoye»: Rezhim dostupa. http://www.yuzhnoe.com/presscenter/media/ photo/techique/launch-vehique.
2. Modelyuvannya ta optimizatsia v nermomechanitsi electroprovidnykh neodnoridnykh til: u 5 t. / Pid. zag. red. akad. NANU R. M. Kushnira. Lvyv: Spolom, 2006–2011. T. 1: Termomechanika bagatokomponentnykh til nyzkoi electroprovodnosti. 2006. 300 p. T. 2: Mechanotermodiffusia v chastkovo prozorykh tilakh. – 2007. 184 p. T. 3: Termopruzhnist’ termochutlyvykh til. 2009. 412 p. T. 4: Termomechanica namagnychuvannykh electroprovodnykh nermochutlyvykh til. 2010. 256 p. T. 5. Optimizatsia ta identifikatsia v termomechanitsi neodnoridnykh til. 2011. 256 p.
3. Prochnost’ materialov I konstruktsiy / Pod obsch. red. acad. NANU V. T. Troschenko. K.: Academperiodika, 2005.1088 p.
4. Bigus G. A. Technicheskaya diagnostica opasnykh proizvodstvennykh obiektov/ G. A. Bigus, Yu. F. Daniev. М.: Nauka, 2010. 415 p.
5. Bigus G. A., Daniev Yu. F., Bystrova N. A., Galkin D. I. Osnovy diagnostiki technicheskykh ustroistv I sooruzheniy. M.: Izdatelstvo MVTU, 2018. 445 p.
6. Birger I. A., Shorr B. F., IosilevichG. B. Raschet na prochnost’ detaley machin: spravochnik. M.: Mashinostroenie, 1993. 640 p.
7. Hudramovich V. S. Ustoichivost’ uprugoplasticheskykh obolochek. K.: Nauk. dumka, 1987. 216 p.
8. Hudramovich V. S. Teoria polzuchesti i ee prilozhenia k raschetu elementov konstruktsiy. K.: Nauk. dumka, 2005. 224 p.
9. Hudramovich V. S., Klimenko D. V., Gart E. L. Vliyanie vyrezov na prochnost’ cylindricheskykh otsekov raketonositeley pri neuprugom deformirovanii materiala/ Kosmichna nauka i technologia. 2017. T. 23, № 6. P. 12–20.
10. Hudramovich V. S., Pereverzev Ye. S. Nesuschaya sposobnost’ sposobnost’ i dolgovechnost’ elementov konstruktsiy. K.: Nauk. dumka, 1981. 284 p.
11. Hudramovich V. S., SIrenko V. N., Klimenko D. V., Daniev Yu. F. Stvorennya metodologii nornativnykh osnov rozrakhunku resursu konstruktsii startovykh sporud ksomichnykh raket-nosiiv / Teoria ta practika ratsionalnogo proektuvannya, vygotovlennya i ekspluatatsii machinobudivnykh konstruktsiy: materialy 6-oy Mizhnar. nauk.-techn. conf. (Lvyv, 2018). Lvyv: Kinpatri LTD, 2018. P. 5–7.
12. Hudramovich V. S., Skalskiy V. R., Selivanov Yu. M. Golografichne ta akustico-emissine diagnostuvannya neodnoridnykh konstruktsiy i materialiv: monografia/Za red. akad. NANU Z. T. Nazarchuka. Lvyv: Prostir-M, 2017. 492 p.
13. Daniev Y. F. Kosmicheskie letatelnye apparaty. Vvedenie v kosmicheskuyu techniku/ Pod obsch. red. A. N. Petrenko. Dnepropetrovsk: ArtPress, 2007. 456 p.
14. O klassifikatsii startovogo oborudovania raketno-kosmicheskykh kompleksov pri obosnovanii norm prochnosti/ A. V. Degtyarev, O. V. Pilipenko, V.S. Hudramovich, V. N. Sirenko, Yu. F. Daniev, D. V. Klimenko, V. P. Poshivalov// Kosmichna nauka i technologia. 2016. T. 22, №1. P. 3–13. https://doi.org/10.15407/knit2016.01.003
15. Karmishin A. V. Osnovy otrabotky raketno -kosmicheskykh konstruktsiy: monografia. M.: Mashinostroenie, 2007. 480 p.
16. Mossakovskiy V. I. Kontaktnyue vzaimodeistvia elementov obolochechnykh konstruktsiy/ Kosmicheskaya technika. Raketnoye vooruzhenie. Space Technology. Missile Armaments. 2019. Vyp. 1 (117) 37. K.: Nauk. dumka, 1988. 288 p.
17. Pereverzev Ye. S. Sluchainye signaly v zadachakh otsenki sostoyaniya technicheskikh system. K.: Nauk. dumka, 1992. 252 p.
18. Prochnost’, resurs, zhivuchest’ i bezopasnost’ mashin/ Otv. red. N. A. Makhutov. M.: Librokom, 2008. 576 p.
19. Technichna diagnostika materialov I konstruktsiy: Dovidn. posibn. u 8 t. / Za red. acad. NANU Z. N. Nazarchuka. T. 1. Ekspluatatsina degradatsia konstruktsiynykh materialiv. Lvyv: Prostir-M, 2016. 360 p.
20. TEchnologicheskie obiekty nazemnoy infrastructury raketno-kosmicheskoy techniki: monografia/ Pod red. I. V. Barmina. M.: Poligrafiks RPK, 2005. Kn. 1. 412 p.; 2006. Kn. 2. 376 p.
21. Нudrаmоvich V. S. Соntact mechanics of shell structures under local loading/ International Аррlied Месhanics. 2009. Vol. 45, № 7. Р. 708– 729. https://doi.org/10.1007/s10778-009-0224-5
22. Нudrаmоvich V. Еlесtroplastic deformation of nonhomogeneous plates / I. Eng. Math. 2013. Vol. 70, Iss. 1. Р. 181–197. https://doi.org/10.1007/s10665-010-9409-5
23. Нudrаmоvich V. S. Mutual influence of openings on strength of shell-type structures under plastic deformation / Strenght of Materials. 2013. Vol. 45, Iss. 1. Р. 1–9. https://doi.org/10.1007/s11223-013-9426-5
24. Mac-Ivily A. J. Analiz avariynykh razrusheniy / Per. s angl. M.: Technosfera, 2010. 416 p.
25. Наrt Е. L. Ргоjесtion-itеrаtive modification оf the method of local variations for problems with a quadratic functional / Journal of Аррlied Мahtematics and Meсhanics. 2016. Vol. 80, Iss. 2. Р. 156–163. https://doi.org/10.1016/j.jappmathmech.2016.06.005
26. Mesarovich M. Teoria ierarkhicheskykh mnogourovnevykh system/ M. Mesarovich, D. Makho, I. Tohakara / Per. s angl. M.: Mir, 1973. 344 p.

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]]> 3.2.2019 Features of design and production of the technological aids for assembly of the spacecraft separation system of CLAMP BAND type https://journal.yuzhnoye.com/content_2019_2-en/annot_3_2_2019-en/ Mon, 15 May 2023 15:45:32 +0000 https://journal.yuzhnoye.com/?page_id=27205
However, during testing of the clamp band assembling technology, jamming of threaded connection as a result of thrust screw turn crush in the area of first turn of insert, gap in the thread after multiple use, scratches and minor scores on the conical surface of pressing mechanism, hardship of work with two wrenches were detected. The material of nut and screw was replaced based on relation between the strength limits: σв of rod > 1.3 σв and nut.
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3. Features of design and production of the technological aids for assembly of the spacecraft separation system of CLAMP BAND type

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Kodenets D. O., Sencha S. A., Makarenko A. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 18-24

DOI: https://doi.org/10.33136/stma2019.02.018

Language: Russian

Annotation: The article deals with the peculiarities of creation of technological crimping device for assembling the spacecraft separation system clamp band. The crimping device is intended to ensure uniform distribution of tension forces in the clamp band belts during assembling of the attachment clamp band, which allows minimizing the load on pyrolocks-pushers and thereby ensuring their operation reliability. The device consists of pressing mechanisms located along circumference symmetrically to the clamp band belts interface plane and fixed on a rest with adjustable supports. The pressing mechanism is a structure with driving kinematic scheme, which allows compensating for mounting errors, unfavorable combination of tolerances, avoiding occurrence of radial load on the thrust screw. However, during testing of the clamp band assembling technology, jamming of threaded connection as a result of thrust screw turn crush in the area of first turn of insert, gap in the thread after multiple use, scratches and minor scores on the conical surface of pressing mechanism, hardship of work with two wrenches were detected. To remove these defects, the sleeve with insert was replaced by the sleeve with protruding part, which allowed distributing the load in all turns more uniformly. The material of nut and screw was replaced based on relation between the strength limits: σв of rod > 1.3 σв and nut. The design of pressing mechanism was changed in respect of connection of thrust screw with hold-down, which allowed decreasing the load on screw pair as a consequence of axial force transfer from screw’s spherical surface to flat surface of hold-down, decreasing the tightening moment to ensure design force of clamp band belts fixation and making the process of pressing mechanisms assembling and disassembling easier. As a result of the updates, the manufacturable and ergonomic structure of crimping device was obtained, the use of which during assembling of the clamp band allows uniformly distributing the crimping forces in clamp band belts, which ensures reliability of spacecraft separation system operation.

Key words: clamp band, half-rings crimping, uniform tension force, pressing mechanism

Bibliography:
1. Birger I. A., Iosilevich G. B. Rezboviye i flantsevye soedineniya. M., 1990. 368 s.
2. Orlov P. I. Osnovy konstruirovania: Sprav.-metod. posobie v 3-kh knigakh. Kn. 1. 2-e izd., pererab. i dop. M., 1977. 623 s.
3. Stanochnye prisposoblenya: Spravochnik. V 2-kh t. M., 1984. T. 1/ Pod red. B. N. Vardashkina, A. A. Shatilova. 1984. 592 s.
4. Pat. 125543 Ukraina, MPK V23R 19/10. Prystriy dlya obtysnennya bandazha kriplennya/ Kodenets D. O., Shevtsova A. I., Shvets’ V. I., Sencha S. A. № u2017 12806; zayvl. 22.12.2017; opubl. 10.05.2018, Byul. № 9.

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China; Pekin; Shenzhen; Nanjing; Nanjing;; Pekin; Shenzhen; Harbin; Pekin;; Shaoxing12
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore12
Germany Falkenstein; Falkenstein;; Munich; Dortmund; Falkenstein6
Brazil; Goiânia; São Carlos; São Paulo; Soledade; São Paulo6
Vietnam; Hanoi;; Ho Chi Minh City; Ha Nam5
France Paris; Paris; Paris; Paris; Paris5
Unknown; Hong Kong; Hong Kong; Hong Kong4
Canada Toronto; Toronto; Monreale; Monreale4
Ukraine Dnipro;2
Netherlands Amsterdam; Amsterdam2
Japan Tokyo;2
Great Britain London; London2
Argentina San Miguel de Tucumán; Isidro Casanova2
The Republic of Korea Seoul1
Italy1
Malaysia1
Iran Tehran1
Iraq Bagdad1
Romania Voluntari1
Finland Helsinki1
Spain Zaragoza1
UAE Abu Dhabi1
Jordan Amman1
Slovakia1
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Збірник науково-технічних статей


Збірник науково-технічних статей


Збірник науково-технічних статей


Збірник науково-технічних статей


Google Scholar - Yuzhnoye State Design Office publications


OpenAlex - Yuzhnoye State Design Office publications


Zenodo - Yuzhnoye State Design Office publications


ROAR - Yuzhnoye State Design Office repository record


ROR - Yuzhnoye State Design Office organization ID


Open Archives - Validate Site


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