Scientific journal TECHNICAL MECHANICS ISSN 1561-9184 (Print), ISSN 2616-6380 (Online) Technical Mechanics is dedicated to advancing scientific knowledge and fostering innovation in the fields of aviation and space engineering, applied mechanics, and material science. Its primary aim is to provide a platform for the dissemination of original research articles, comprehensive reviews, and theoretical developments that contribute to the progress of engineering sciences and their practical applications. In 1993, the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine started to publish an interdepartmental collection of scientific papers entitled Tekhnichna Mekhanika (the Ukrainian for technical mechanics), which in September 1997 received the status of a scientific journal. In 2017, the institute received a new state registration certificate, according to which the journal has the official English title of Technical Mechanics and has the right to publish papers in English and to be distributed internationally. The journal publishes papers in Ukrainian and English (at authors’ choice). The journal is indexed in Google Scholar та Index Copernicus. The journal is sent to the V. I. Vernadsky National Library of Ukraine to be placed in the Scientific Periodicals of Ukraine database. All papers are assigned a DOI (CrossRef). DOI prefix: 10.15407/itm Abbreviated title: Teh. Meh.; ТМ. Authors retain copyright to their materials published in Technical Mechanics, and the journal does not claim any intellectual property rights to the authors’ content. Authors may deposit the final version of their paper in institutional or any other repositories where the paper will be in open access (at their own choice). Technical Mechanics is in diamond open access, i.e., free both for authors to publish in and for readers to access all papers and issues. Once published, all papers are immediately in open access for reading, downloading, and use without any technical limitations, i.e., without any access delay. The Editorial Board of Technical Mechanics is guided by international ethical standards for scientific publications and adheres to an open access policy. All submitted papers are to be peer-reviewed and checked for plagiarism. Starting with June 2026, the journal is to publish papers of the Mechanical Engineering and Machine Building cluster: G 8 Material Science; G 9 Applied Mechanics; G 12 Aeronautical and Space-Rocket Engineering. Journal website: https://journal-itm.dp.ua Media identifier in the Register of Subjects in the Media Field: R30-03759 In 2020, the journal was included in the list of Ukrainian specialized scientific editions (category B) by the Ministry of Education and Science of Ukraine’s orders No. 886 of July 2, 2020, and No. 1188 of September 24, 2020, in: 113 Applied Mathematics; 131 Applied Mechanics; 134 Aeronautical and Space-Rocket Engineering; 151 Automation and Computer-Integrated Technologies; 104 Physics and Astronomy. Frequency: 4 issues a year Founders: Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine ​ National Academy of Sciences of Ukraine Publisher: Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine ROR ID: https://ror.org/003ed9546 National Joint Register Code: 05539962 Publisher website: https://itm.dp.ua
ANALYSIS OF THE STRAIN OF A SUBSOILER CHAIN LINK AND ITS FORMING BEHAVIOR UNDER STATIC LOADING
DOI: https://doi.org/10.15407/itm2026.02.088 Optimizing the regulated safety factor and service life of load round-link chains is an important national economic task, given their wide range of application in machine structures and technological equipment. The goal of this study is to investigate the strain of round-link chain links and to substantiate criteria for the end of their service life. Mechanical testing was performed using specially prepared five-link specimens of short-link and long-link Grade G80 load chains with diameters of 3, 4, 5, 6, and 8 mm manufactured from 20MnNiCrMo5-2 steel in accordance with ASTM A391. A static axial load on the chain specimens was simulated by a gradual monotonic increase in force from zero up to the failure of one of the specimen links using an R-50M1 tensile testing machine. A basis for developing recommendations on defect detection criteria for chains under operational loading by external forces was a methodology based on comparing the equivalent (or principal) logarithmic strain obtained experimentally with that determined according to the Hencky and the Swainger criteria. The results of shape transformation of round-link chain links are presented. Absolute and relative values of the deformation and contour shape and overall dimension change of short-link and long-link load chains with diameters of 3, 4, 5, 6, and 8 mm were determined. Based on a comparison between the shape change measure of the infinitesimal deformation approximation according to the Hencky and the Swainger criteria and experimentally determined limiting values of pitch deformation in load round-link chains, a unified rejection criterion independent of chain diameter was established. It is proposed to set the absolute value of this criterion at ||12,5х10-3||. REFERENCES 1. Getun G. V., Bezlubenko I. S., Balina O. I., Butsenko Yu. P. Construction principles and features static calculation of arcs. Spatial Development. 2022. No. 1. Pp. 43-55. (In Ukrainian). https://doi.org/10.32347/2786-7269.2022.1.43-55 2. Shevchenko V. D., Piskunov V. H., Fedorenko Yu. M. et al. Structural Mechanics of Metal Structures of Road-Building, Hoisting, and Transport Machines. Piskunov V. H. Piskunov, V. D. Shevchenko (Eds.). Kyiv: Vyshcha Shkola, 2004. 438 с. (In Ukrainian). 3. Bezklubenko I., Geptun G. Chain line as an optimum form for stable structures. Urban Development and Spatial Planning. Kyiv: Kyiv National University of Construction and Architecture, 2025. No. 90. Pp. 285-315. URL: http://mtp.knuba.edu.ua/issue/archive (Last accessed on March 19, 2026). (In Ukrainian). 4. Troshchenko V. T. Deformation and Destruction of Metals Under Multicycle Loading. Kyiv: Naukova Dumka, 1981. 343 pp. 5. Troshchenko V. T., Khamaza L. A. Nonlocalized and localized fatigue damage in metals and alloys. Visnyk TNTU. 2014. V. 76. No. 4. Pp. 7-21. URL: https://elartu.tntu.edu.ua (Last accessed on March 29, 2026). 6. Troshchenko V.T. Fatigue of metals under nonuniform stress. Message 1. Stress assessment methods and research results. Strength of Materials. 2010. No. 2. Pp. 5-24. https://doi.org/10.1007/s11223-010-9200-x 7. Yarosh Ya., Sheludchenko B., Kondratiuk A., Biletskiy V., Pluzhnikov O. (2020). In a building visual-plastic environment the equal "chain line" moving flexible lines. Scientific Horizons. 2020. V. 23. No. 4. Pp. 65-71. (In Ukrainian).https://doi.org/10.33249/2663-2144-2020-89-4-65-71 8. Kondratiuk A., Šarauskis E., Sheludchenko B., Kukharets S., Jasinskas A., Zabrodskyi P., Shubenko V. Substantiation of the use of a flexible chain-type subsoiler for improving the agrotechnological properties of soil. Sustainability. 2024. V. 16. Art. 5355. 9. Nadykto V., Domeika R., Golub G., Kukharets S., Chorna T., Česna J., Hutsol T. Research on a machine-tractor unit for strip-till technology. AgriEngineering. 2023. V. 5. Pp. 2184-2195. 10. Sheludchenko B. А., Biletsky V. R., Borovsky V. M., Pluzhnikov O. В., Trosteniuk Y. V. Studies generalization of shape change of equipotential surfaces of stress-deformed objects. Technical Engineering. 2023. No. 1 (91). Pp. 110-118. (In Ukrainian). 11. Sheludchenko B., Syvak B., Pluzhnikov O. Forming Dynamics in Conditions of a Compound Stress. Saarbrücken: LAP LAMBERT Academic Publishing, 2015. 156 pp. (In Ukrainian).
MATHEMATICAL SIMULATION OF THE STRESS AND STRAIN FIELD OF HIP JOINT ELEMENTS UNDER STATIC LOADS AT DIFFERENT STAGES AFTER A TOTAL HIP ARTHROPLASTY
DOI: https://doi.org/10.15407/itm2026.02.098 An important problem in applied biomechanics involving total hip arthroplasty is to ensure the stable endoprosthesis operation using the results of mathematical simulation of acetabular component – acetabulum interaction. Th goal of this study is to develop finite-element models based on computer tomography data to assess the stress and strain field (SSF) of hip joint elements under service loads after a total arthroplasty. Based on computer tomography data, finite-element models are developed to assess the stress and strain field of hip joint elements at different stages after a total press-fit arthroplasty with the use of a cementless acetabular component pressed into an intact acetabulum. Two stages are considered; an initial stage immediately after the arthroplasty and a stage of full healing. For the initial stage, different variants of endoprosthesis mounting with account for the presence or absence of subchondral tissue fragments on the acetabulum bottom are considered. For the full healing stage, account is made for adhesion, i.e., the subchondral tissue of the acetabulum growing into the acetabular component surface. The finite-element models developed account for a surface-surface frictionless contact between the hip joint endoprosthesis head and the acetabular component liner, a friction contact between the metal body and the liner, and a contact with the joint motion of the bone tissue contact surfaces in their interaction. Contact interaction between the metal body and the bone tissues of the acetabulum bottom is accounted for as a friction contact at the initial stage and as a contact with the joint motion of the contact surfaces at the full healing stage. The paper presents the results on the SSF of intact-acetabulum hip joint elements after a total arthroplasty for the case of two-leg standing. The proposed models may be used as a basis for further studies of the in-service SSF of hip joint elements after a total arthroplasty with account for acetabulum defects. REFERENCES 1. Netter F. Anthropotomy Atlas. Lviv: Nautilus, 2004. 592 pp. (In Ukrainian). 2. Hip Arthroplasty. A. E. Loskutov (Ed.). Dnipro: Lira, 2010. 344 pp. (In Ukrainian). 3. Total hip arthroplasty methods. URL: https://www.statpearls.com/articlelibrary/viewarticle/22894/ (Last accessed on June 17, 2026). (In Ukrainian). 4. Total hip replacement surgery (hip prosthesis). URL: https://www.joint-surgeon.com/orthopedic-services/osteoarthritis-of-the-hip/total-hip-replacement/ (Last accessed on June 17, 2026). 5. Current views on arthroplasty. URL: https://www.vz.kiev.ua/suchasni-poglyadi-na-endoprotezuvannya/ (Last accessed on June 17, 2026). (In Ukrainian). 6. Hip arthroplasty (hip joint replacement). URL: https://medicalplaza.ua/uk/content/endoprotezirovanie-tazobedrennogo-sustava (Last accessed on June 17, 2026). (In Ukrainian). 7. Hip joint endoprosthesis: an individual model and material selection for a patient. URL: https://ortoped-klinik.com/orthopedic-services/osteoarthritis-of-the-hip/modeli-endoprotezov-tazobedrennogo-sustava.html (Last accessed on June 17, 2026). (In Russian). 8. Imbuldeniya A. M., Walter W. L., Zicat B. A., Walter W. K. Cementless total hip replacement without femoral osteotomy in patients with severe developmental dysplasia of the hip. Minimum 15-year clinical and radiological results. Bone Joint J. 2014. V. 96-B. No. 11. Pp. 1449-1454. https://doi.org/10.1302/0301-620X.96B6.33381 9. Scuderi R. Techniques in Revision Hip and Knee Arthroplasty. Philadelphia: Elsevier, 2014. 608 pp. 10. Horst P., Sproul R. C., Bozic K. J. The economics of total hip and knee arthroplasty. In: Scuderi R. Techniques in Revision Hip and Knee Arthroplasty. Philadelphia: Elsevier, 2015. Pp. 2-5. 11. Wong K. C., Kumta S. M., Geel N. V., Demol J. One-step reconstruction with a 3D-printed, biomechanically evaluated custom implant after complex pelvic tumor resection. Computer Aided Surgery. 2015. V. 20. No. 1. Pp. 14-23. https://doi.org/10.3109/10929088.2015.1076039 12. Loskutov A. E. Development of modular hip arthroplasty by ORTEN home systems. Modern Medical Technology. 2011. No. 3-4. Pp. 207-210. (In Russian). 13. Loskutovv O. Ye., Oliinyk O. Ye., Loskutov O. O., Syniehubov D. A. Development of the national arthroplasty (the results of thirty-year studies). Transplantation and Artificial Organs. 2021. No. 2(03). Pp. 28 - 36. (In Ukrainian). 14. Ukrstat. Databank. URL: https://stat.gov.ua/uk/explorer?urn=SSSU%3ADF_SURVEY_LIVING_CONDITIONS_HOUSEHOLDS_A%28~%29&filter=IDX_BODY_MASS (Last accessed on June 17, 2026). 15. Horobets D. V., Sobolevska M. B., Loskutov O. Ye. Finite-element simulation of the in-service stress and strain field of hip joint elements based on computer tomography data. Teh. Meh. 2026. No. 1. Pp. 73-85. (In Ukrainian). https://doi.org/10.15407/itm2026.01.073 16. Zienkiewicz O. The Finite Element Method in Engineering Science. Moscow: Mir, 1975. 541 pp. (In Russian). 17. Aleksandrov A. V., Potapov V. D. Fundamentals of the Elasticity and Plasticity Theory. Moscow: Vysshaya Shkola, 1990. 400 pp. (In Russian). 18. Kaplun A. B. Ansys in the Engineer's Hands: Manual. Moscow: Editorial URSS, 2003. 272 pp. (In Russian).
FEATURES OF THE AERODYNAMIC OPTIMIZATION OF THE SPATIAL SHAPE OF AXIAL-FLOW COMPRESSOR BLADES
DOI: https://doi.org/10.15407/itm2026.02.003 This paper is concerned with the choice of rational methods for the aerodynamic improvement of blade rows of gas-turbine engines’ highly loaded axial-flow compressor stages. The paper presents an assessment of capabilities of an approach to the aerodynamic optimization of compressor blade rows developed at the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine. Its major constituents are a numerical simulation of a 3D blade row flow based on the сcomplete averaged Navier-Stokes and a two-parameter turbulence model; the use of sufficiently “coarse” computational grids, for which, however, the computed results are sensitive to blade shape variation; the formulation of quality criteria as aerodynamic characteristics of blade rows averaged over the airflow rate; a search for an optimum spatial blade shape using the points of sequences evenly distributed in the space of variables; and a simple method of blade shape variation for which the blade shape remains aerodynamically acceptable in the optimization process. The goal of the work is to identify the features that manifest themselves in that approach and assess the possibility of optimization time reduction by accounting for them. Use was made of numerical data obtained earlier in the aerodynamic stabilization of compressor impeller blades. An information-analytical assessment of the data is presented. It is shown that the optimization improves the aerodynamic characteristics of cascades for the hub, the middle, and the peripheral region of the blade row channel, Varying the blade shape in the course of the optimization process keeps it aerodynamically acceptable too. The results obtained show the advisability of using small sets of pre-optimized 2D cascades in 3D compressor blade shaping to reduce the optimization time. REFERENCES 1. Ashihara K., Goto A. Turbomachinery blade design using 3-D inverse design method, CFD and optimization algorithm. Proc. of ASME TURBO EXPO 2001. (New Orleans, Louisiana, USA, June 4-7, 2001). New Orleans (USA), 2001. 9 pp. https://doi.org/10.1115/2001-GT-0358 2. Chan-Sol Ahn, Kwang-Yong Kim. Aerodynamic design optimization of an axial flow compressor rotor. Proc. of ASME TURBO EXPO 2002. (Amsterdam, The Netherlands, June 3-6, 2002). Amsterdam (The Netherlands), 2002. 7 pp. 3. Sivashanmugam V. K., Arabnia M., Ghaly W. Aero-structural optimization of an axial turbine stage in three-dimensional flow. Proc. of ASME TURBO EXPO 2010. (Glasgow, UK, June 14-18, 2010). Glasgow (UK), 2010. 14 pp. 4. Ershov S. V., Yakovlev V. A. Aerodynamic optimization of the spatial shape of gas and steam turbine blades. Aerospace Technic and Technology. 2008. No. 7. Pp. 66-70. (In Russian). 5. Menyalov A.V., Tronchuk A. A., Ugryumova E. M. Application of evolutionary methods to the solution of gas-turbine engine compressor optimization problems. Aerospace Technic and Technology. 2008. No. 5. Pp. 59-65. (In Russian). 6. Jinguang Yang, Xiuquan Huang, Hu Wu. Multi-row inverse method based on the adjoint optimization. Proc. of ASME TURBO EXPO 2011. (Vancouver, British Columbia, Canada, June 6-10, 2011). Vancouver, British Columbia (Canada), 2011. 11 pp. 7. Rongye Zheng, Jianhua Xiang, Jinju Sun. Blade geometry optimization for axial flow compressor. Proc. of ASME TURBO EXPO 2010. (Glasgow, UK, June 14-18, 2010). Glasgow (UK), 2010. 12 pp. 8. Xu C., Amano R. S. A turbine airfoil aerodynamic design process. Proc. of ASME TURBO EXPO 2001. (New Orleans, Louisiana, USA, June 4-7, 2001). New Orleans (USA), 2001. 10 pp. 9. Melashich S. V. Parametric description method for compressor cascade airfoils. Teh. Meh. 2012. No. 2. Pp. 77-82. (In Russian). 10. Jinxin Cheng, Zhaohui Dong, Shengfeng Zhao, Hang Xiang. Research on aerodynamic optimization method of multistage axial compressor under multiple working conditions based on phased parameterization strategy. Mathematical Problems in Engineering. 2021. URL: https://www.hindawi.com/journals/mpe/2021/5518507/ (Last accessed on May 17, 2026). https://doi.org/10.1155/2021/5518507 11. Schnoes M., Voß C., Nicke E. Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils. J. Glob. Power Propuls. Soc. 2018. V. 2. Pp. 516-528. https://doi.org/10.22261/JGPPS.W5N91I 12. Shelkovsky M. Yu. Aerodynamic improvement of ten-stage axial-flow compressor for a stationary gas-turbine engine. Aerospace Technic and Technology. 2014. No. 9. Pp. 27-32. (In Russian). 13. Matveev V. N., Baturin O. V., Popov G. M. Multistage compressor uprating by optimization methods. Aerospace Technic and Technology. 2013. No. 8. Pp. 103-107. (In Russian). 14. Borisenko V. D., Ustenko S. A., Ustenko I. V., Kuzma K. T. Geometric modeling of the blade airfoil of an axial flow compressor of the S-shaped form. Applied Questions of Mathematical Modelling. 2020. V. 3. No. 2.2. Pp. 24-34. (In Ukrainian). 15. Suder K. L. NASA's Role in gas turbine technology development: Accelerating technical progress via collaboration between academia, industry, and government agencies. Proc. of ASME TURBO EXPO 2019. (Phoenix, Arizona, USA, June 17-21, 2019). Phoenix (USA), 2019. 29 pp. https://doi.org/10.1115/GT2019-91539 16. Dulepov A. A., Balalaiev A. V. Simulation of the flow in the fan stage of a turbofan engine with annular grooves casing treatmen. Aerospace Technic and Technology. 2024. No. 4sup2. Pp. 5-11. (In Ukrainian). https://doi.org/10.32620/aktt.2024.4sup2.01 17. Kvasha Yu. A. Calculation of 3D turbulent flow in supersonic compressor stage blade channels. Teh. Meh. 1999. No. 1. Pp. 9-13. (In Russian). 18. Kvasha Yu. A., Zinevich N. A. On the choice of computational grids in the numerical simulation of 3D turbulent flows in supersonic compressor stage wheels. Teh. Meh. 2013. No. 3. Pp. 34-41. (In Russian). 19. Sobol I. M., Statnikov R. B. Optimum Parameter Choice in Multicriterion Problems. Moscow: Nauka, 1981. 110 pp. (In Russian). 20. Kvasha Yu. A., Zinevich N. A. Aerodynamic optimization of spatial form of impeller blade of supersonic compressor stage. Teh. Meh. 2016. No. 3. Pp. 35-42. (In Russian). 21. Kvasha Yu. A., Zinevych N. A., Petrushenko N. V. Features of blade shape variation in the aerodynamic improvement of aircraft gas-turbine engine compressors. Teh. Meh. 2022. No. 2. Pp. 17-24. (In Ukrainian). https://doi.org/10.15407/itm2022.02.017 22. Design and Overall Performance of Four Highly Loaded, High-Speed Inlet Stages for an Advanced High-Pressure-Ratio Core Compressor: NASA Technical Paper 1337, 1978. 132 pp.
AEROSTATIC SYSTEMS IN DEFENSE APPLICATIONS: THE CURRENT CHALLENGES AND THE STATE OF THE ART
DOI: https://doi.org/10.15407/itm2026.02.010 Aerostatic systems of the airship type have more than a century of engineering development and continue to attract attention within the scientific and technical community today. On the one hand, this can be explained by the fact that lighter-than-air vehicles require lower fuel consumption and onboard energy to maintain their position in the airspace. On the other hand, optimal airship configurations may be effective means of cargo transportation and platforms for equipment of various purposes, including scientific, meteorological, and military payloads. Considering these factors, this paper analyzes the state of the art in the development of aerostatic and airship systems for various applications. Based on this analysis, the paper identifies the advantages and drawbacks of using lighter-than-air vehicles in the Earth’s dense atmosphere and challenges associated with their use for different purposes. It is also shown that airship systems can serve as an effective element of air defense systems against hazardous unmanned aerial vehicles. In this context, the objective of this study is to identify key challenges in the design of airship systems intended for the protection of Ukraine’s critical infrastructure against dangerous unmanned aerial vehicles. To achieve this objective, the paper analyzes the state of the art in the development of materials for envelopes and structural elements of modern airships, the features of navigation and control system development, and the payload capacity depending on the aerostat geometry. As a result, technical requirements for the development of airship-type aerostatic systems for airspace and critical infrastructure protection are formulated, and lines of further research aimed at resolving the key challenges in the design of such systems are identified. REFERENCES 1. Manikandan M., Pant R.S. Research and advancements in hybrid airships-A review. Progress in Aerospace Sciences. 2021. V. 127. Art. 100741. https://doi.org/10.1016/j.paerosci.2021.100741 2. Dasaradhan B., Das B.R., Sinha M.K., Kumar K., Kishore B., Prasad N. E. A brief review of technology and materials for aerostat application. Asian Journal of Textile. 2018. V. 8. Pp. 1-12. https://doi.org/10.3923/ajt.2018.1.12 3. GAO, Defense acquisitions: Future aerostat and airship investment decisions drive oversight and coordination needs, United States Government Accountability Office, Report GAO-13-81, Washington D.C., 2012, 69 pp. URL: https://www.gao.gov/assets/gao-13-81.pdf (Last accessed on March 25, 2026). 4. Byelyaev D.M., Rasstryghin O.O., Semeniuk R.P., Bunakov V.P., Analysis of the world's experience in the use of military aerostat aircraft and prospects for their use in the Armed Forces of Ukraine. Ozbroyennia ta Viiskova Tekhnika.2015. V. 7. No. 3. Pp. 67-72. (In Ukrainian). https://doi.org/10.34169/2414-0651.2015.3(7).67-72 5. Kumar A., Sati S.C., Ghosh A.K., Design, testing, and realisation of a medium size aerostat envelope, Defence Science Journal. 2016. V. 66. No. 2. Pp. 93-99. 6. Orlov V.V., Korkin O.Yu., Kovalishin S.S., Naumov O.I., Placement of robotic missile defense complexes on an unmanned air vehicle. Zbirnyk Naukovykh Prats Viiskovoi Akademii. 2023. No. 2 (20). Pp. 108-116. (In Ukrainian). https://doi.org/10.37129/2313-7509.2023.20.108-116 7. Frontliner / Texty.org.ua, Drones on an aerostat: Ukraine is developing a new complex to counter Shaheds. 2025. URL: https://texty.org.ua/fragments/114662/drony-na-aerostati-v-ukrayini-rozroblyayut-novyj-kompleks-dlya-protydiyi-shahedam-foto/ (Last accessed on March 25, 2026). 8. Carrión M., Steijl R., Barakos G.N., Stewart D., Analysis of hybrid air vehicles using computational fluid dynamics. Journal of Aircraft. 2016. 2016. V. 53. No. 4. Pp. 1001-1012. https://doi.org/10.2514/1.C033402 9. Pai A., Manikandan M. A comparative study of aerodynamic characteristics of conventional and multi-lobed airships. The Aeronautical Journal. 2025. V. 129. Pp. 2435-2459. https://doi.org/10.1017/aer.2025.39 10. Lv J., Zhou Y., Zhang Y., Nie Y., Wang Q. Study of performance of aerostat envelope materials on the coast. Frontiers in Materials. 2022. V. 9. Art. 992984. https://doi.org/10.3389/fmats.2022.992984 11. Kayenzemale J. I., Ibwe K. S. Energy-efficient tethered aerostat platforms for providing last-mile connectivity in national parks. Journal of Electrical Systems and Information Technology. 2025. V. 12. Art. 7. https://doi.org/10.1186/s43067-025-00197-x 12. Ram C. V., Pant R. S. Multidisciplinary shape optimization of aerostat envelopes. Journal of Aircraft. 2010. V. 47. Pp. 1073-1076. https://doi.org/10.2514/1.46744 13. Rajani A., Pant R. S., Sudhakar K. Dynamic stability analysis of a tethered aerostat. Journal of Aircraft. 2010. V. 47. Pp. 1531-1538. https://doi.org/10.2514/1.47010 14. Adak B., Joshi M. Coated or laminated textiles for aerostat and stratospheric airship. In: Advanced Textile Engineering Materials. H. R. Mattila (Ed.). Hoboken: Wiley. 2018. Pp. 191-214. https://doi.org/10.1002/9781119488101.ch7 15. Kim D.-M. et al. Mechanical property characterization of film-fabric laminate for stratospheric airship envelope. Composite Structures. 2007. V. 79. No. 3. Pp. 351-359. 16. Cao M., Qu S., Li J., Lv M. Thermoelasticity of a fabric membrane composite for the stratospheric airship envelope based on multiscale models. Applied Composite Materials. 2017. V. 24. No. 1. Pp. 209-220. https://doi.org/10.1007/s10443-016-9522-3 17. Liggett P. E., Carter D. L., Dunne A. L., Darjee D. H., Placko G. W., Mascolino A. I., McEowen L. J. Metallized flexible laminate material for lighter-than-air vehicles. US Patent US8524621B2. 2013. Pp. 1-10. 18. Zhai H., Euler A. Material challenges for lighter-than-air systems in high altitude applications. AIAA Aviation, Technology, Integration and Operations Conference (ATIO). 2005. Pp. 1-12. https://doi.org/10.2514/6.2005-7488 19. Lai Z., Tang M., Hu X., Shu X., Huang W., Pan Y. Dynamics modeling and motion evaluation of a near-ground tethered balloon cable system under severe wind environments. Actuators. 2024. V. 13. No. 10. Art. 402. https://doi.org/10.3390/act13100402 20. Stockbridge C., Ceruti A., Marzocca P. Airship research and development in the areas of design, structures, dynamics and energy systems. Int. J. of Aeronaut. Space Sci. 2012. V. 13. Iss. 2. Pp. 170-187. https://doi.org/10.5139/IJASS.2012.13.2.170 21. Pillai A.S., Oruganti V.R.M. Modelling and simulation of aerodynamic parameters of an airship. Advances in Science, Technology and Engineering Systems Journal. 2020. V. 5. Pp. 167-176. https://doi.org/10.25046/aj050420 22. Husynin V. P., Husynin A. V. Dirigible Aeronautics. Kyiv: Kafedra, 2012. 364 pp. (In Ukrainian). 23. Mano S., Ajay Sriram R., Vinayagamurthy G., Nadaraja Pillai S., Pasha A.A., Reddy D.S.K., Rahman M.M. Effect of a circular slot on hybrid airship aerodynamic characteristics. Aerospace. 2021. V. 8. No. 6. Art. 166. https://doi.org/10.3390/aerospace8060166 24. Zhang L., Lv M., Sun C., Meng J. Flight performance analysis of hybrid airship considering added mass effects. Journal of Dynamic Systems, Measurement and Control, Transactions of the ASME. 2018. V. 140. Art. 111001. https://doi.org/10.1115/1.4040220 25. Gomes S. B. V., Ramos J. G. Airship dynamic modeling for autonomous operation. Proceedings of the IEEE International Conference on Robotics and Automation. 1998. Pp. 3462-3467. https://doi.org/10.1109/ROBOT.1998.680973
DEPLOYMENT OF THE ROTATING TWO BODIES TETHER IN AN ORBIT
DOI: https://doi.org/10.15407/itm2026.02.023 The focus of the study is a compact orbital tether consisting of two bodies that must be deployed from a spacecraft so that after deployment it rotates at a constant angular speed and attains a prescribed length. The end masses are taken as equal, and the connecting cable is assumed massless. The aim of the research is to develop a feedforward control for the tether length, taking into account the gravitational torque exerted by the central Newtonian field of forces. Initial rotation of the tether about the orbit’s binormal is employed for deployment. The research consists of two stages. The development of the control law is based on the tether length in the first stage, which provides the performance of the desired deployment. The tether motion equations, expressed in spherical polar coordinates for a particular case of tether motion in the orbital plane, are used at this stage. In the second investigative phase, a numerical simulation of the deployment dynamics of a tether under the effect of the developed feedforward control law is performed using the tether length. As a mathematical model of the tether, the full set of motion equations for a variable‑length tether in spherical polar coordinates is employed, describing the spatial motion of bodies. The tensile force of the cable entering these equations is described by the control law governing length variation and its first two time derivatives. The novelty of this study lies in devising a feedforward control law that treats the tether as an underactuated mechanical system. Analytical mechanics, numerical techniques, and authors‑developed methods were employed in this research. The results enable determination of the permissible ranges of deployment parameters, facilitating this type of deployment. Practically, the findings allow small tethers to be deployed in orbit and brought to uniform rotation at a specified length via tether length control. REFERENCES 1. Alpatov A. P., Beletsky V. V., Dranovskii V. I., Khoroshilov V. S. et al. Dynamics of Tethered Space Systems. Advances in Engineering. Boca Raton: CRC Press, 2010. 223 pp. 2. Alpatov A. P., Zakrzhevskii A. E. Passive deployment of a tether between two bodies in orbit. International Applied Mechanics. 1999. V. 35. No.10. Pp. 1053-1058. https://doi.org/10.1007/BF02682318 3. Beletsky V. V. Motion of an artificial satellite about its center of mass. Jerusalem: Israel Program for Scientific Translations. 1966. 4. Beletsky V. V., Levin E. M. Dynamics of Space Tether Systems. V. 83. Advances in the Astronautical Sciences, San Diego: Univelt, 1993. 499 pp. 5. Huang P., Zhang F., Chen L. et al. A review of space tether in new applications. Nonlinear Dynam. 2018. V. 94. Pp. 1-19. 6. Kang J., Zhu Z., Santaguida L. F. Analytical and experimental investigation of stabilizing rotating uncooperative target by tethered space tug. IEEE Trans. Aero. Electron. Syst. 2021. V. 57. No. 4. Pp. 2426-2437. https://doi.org/10.1109/TAES.2021.3061798 7. Li Z., Meng Z., Huang P. Spin-up control of tethered space station for artificial gravity task. IEEE International Conference on Robotics and Biomimetics (ROBIO). 2019. Pp. 2502-2508. https://doi.org/10.1109/ROBIO49542.2019.8961375 8. Rajkumar A., Bannova O. A three-body spacecraft as a testbed for artificially-induced gravity research in low earth orbit. 2020. ARC AIAA. 2020-4110. https://doi.org/10.2514/6.2020-4110 9. Trushlyakov V.I., Yudintsev V.V. Rotary space tether system for active debris removal. J. Guid. Control Dynam. 2020. V. 43. No. 2. Pp. 354-364. https://doi.org/10.2514/1.G004615 10. Wang Ch., Zakrzhevskiy O. E. Deployment of the space tether in the centrifugal force field with alignment to the local vertical. Teh. Meh. 2024. No.1. Pp. 26-39. https://doi.org/10.15407/itm2024.01.026 11. Zakrzhevskii A. E. Method of deployment of a space tethered system aligned to the local vertical. J. of Astronaut. Sci. 2016. V. 63. Pp. 221-236. https://doi.org/10.1007/s40295-016-0087-z
ANALYSIS OF THE MAGNETIC FIELD AND THE MAGNETIC FLUX IN SPACECRAFT’S PASSIVE DEORBIT SYSTEMS
DOI: https://doi.org/10.15407/itm2026.02.038 The rapid growth in the number of objects in low-Earth orbits and the active deployment of large satellite constellations are making the problem of near-Earth space debris increasingly critical. Current international regulations limit the post-mission orbital lifetime of a spacecraft to 5 years, making the issue of reliable and simple deorbit ever more relevant, especially for small spacecraft. Traditional active propulsion systems require significant propellant and power resources and increase system complexity, which is critical for small spacecraft. This drives the development of passive methods, among which the use of magnetic systems interacting with the ionospheric plasma is promising. This paper presents the results of a study on coaxial assemblies of permanent magnets as the core element of a passive deorbit system. The concept is based on the interaction between the magnetic field generated by the magnets and charged particles in the plasma, which leads to momentum exchange and the generation of a force opposing the spacecraft’s motion. The effectiveness of this approach is largely determined not only by the magnitude of the magnetic field, but also by its spatial distribution, particularly by the total magnetic flux. The object of this study is a coaxial magnetic system consisting of a steel flange, outer neodymium ring magnets, and central cylindrical magnets. Six variants of coaxial configurations were considered, differing in the geometric dimensions of the central magnets (15, 20, and 30 mm) and in their pole orientations (S–S–S and S–N–S). For each configuration, the magnetic field distribution and magnetic flux were evaluated using computer simulation. The simulation results show that the S–N–S configuration increases the magnetic flux by 7–12.5% compared to the S–S–S configuration at identical overall dimensions of the magnetic system. Doubling the diameter of the central element provides an approximately 23% increase in flux, thus confirming the effectiveness of scaling the inner part of the assembly. This highlights the importance of optimizing the magnetic field topology and demonstrates that compact passive magnetic systems are promising for deorbiting applications. REFERENCES 1. ESA's Annual Space Environment Report. GEN-DB-LOG-00288-OPS-SD. Issue 9, Rev. 1. European Space Agency, Space Debris Office. 2025. 118 pp. URL: https://www.sdo.esoc.esa.int/publications/Space_Environment_Report_I9R1_20251021.pdf (Last accessed on April 20, 2026). 2. Space Sustainability Report. Inmarsat. 2022. 54 pp. URL: https://www.ukspace.org/wp-content/uploads/2022/06/Inmarsat-Space-Sustainability-Report.pdf (Last accessed on April 20, 2026). 3. Mitigation of Orbital Debris in the New Space Age: Second Report and Order, FCC 22-74, Federal Communications Commission. 2022. 54 pp. URL: https://docs.fcc.gov/public/attachments/FCC-22-74A1.pdf (Last accessed on April 20, 2026). 4. ESA Space Debris Mitigation Requirements. ESSB-ST-U-007. Issue 1, Rev. 1. European Space Agency, ESB Secretariat. 2025. 80 pp. URL: https://esamultimedia.esa.int/docs/technology/ESSB-ST-U-007_Issue_1_Rev_1(23_October_2025).pdf (Last accessed on April 20, 2026). 5. Аbaturov А. O., Dron М. M., Kulyk О. V., Proroka V. A. An overview of methods and technical means of space debris removal from low earth orbits. System Design and Analysis of Aerospace Technique Characteristics. 2022. V. 31. No. 2. Pp. 3-13. https://doi.org/10.15421/472209 6. Muhammad H. J., Akhlaq A. Space Debris Removal Using Electromagnetic Fields. Preprint (Version 1) available at Research Square. April 2026. 7. Shuvalov V. A., Simanov V. G., Horolsky P. G., Kulagin S. N. Deceleration of an artificially magnetized spacecraft in the ionospheric plasma. Space Sci. & Technol. 2020. V. 26. No. 2. Pp. 59-71. (In Russian). https://doi.org/10.15407/knit2020.02.059 8. Shuvalov V. A., Gorev N. B., Tokmak N. A., Kuchugurnyi Y. P. Drag on a spacecraft produced by the interaction of its magnetic field with the Earth's ionosphere. Physical modelling. Acta Astronautica. 2020. V. 166. Pp. 41-51. https://doi.org/10.1016/j.actaastro.2019.10.018
ELECTROJET THRUSTER TO BALANCE AN AERODYNAMIC DRAG ON A SMALL SPACECRAFT IN A VERY LOW EARTH ORBIT
DOI: https://doi.org/10.15407/itm2026.02.049 The goal of this paper is to study the feasibility of an electrojet thruster for a long-term operation in a very low Earth orbit. The paper presents the advantages of very low orbits and substantiates the importance of their exploitation. The main obstacle to their use is a gas-dynamic drag on a spacecraft in the Earth‘s upper atmosphere. At present, the dominant concept of its balancing is to employ an electrojet thruster that uses the surrounding gas to produce a balancing thrust. In developing a thrust system of this type, the principal task is to design a device for collecting a sufficient gas amount from the surrounding atmosphere. However, in the course of development it turned out that the properties of the upper atmosphere components do not allow one to produce a thrust sufficient for atmospheric drag balancing. The existing gas collection systems proved to be incapable of providing the required gas accumulation rate. The paper proposes an alternative concept of an electrojet thruster for atmospheric drag balancing, which is based on the author’s experience in the development of plasma devices for the deposition of functional metal coatings. The paper analyzes the possibility of replacing a propellant gas for an electrojet thruster with a condensed working medium: a metal. For this purpose, the concept of a hybrid electrojet thuster is developed. The concept is based on combining a vacuum arc discharge and a magnetron discharge in a single plasma device. A pulsed vacuum arc discharge serves as an electron source to initiate and maintain a gasless magnetron self-sputtering discharge. In this case, the arc device can produce a microthrust. The main thrust is produced in the magnetron device by metal sputtering, ionization, and ion acceleration. In the joint operation of both discharges, the magnetron discharge implements a gasless magnetron self-sputtering mode, which is similar to the BP HiPIMS bipolar high-current pulsed magnetron sputtering mode. A conceptual plasma device model is developed to verify the feasibility of a hybrid electrojet thruster. The preliminary results confirm the operability of the plasma device arrangement and the feasibility of a gasless thrust system as an alternative to the existing concept. REFERENCES 1. Crisp N. H., Roberts P. E., Livadiotti S. The benefits of very low earth orbit for earth observation missions. Progress in Aerospace. 2020. V. 117. Art. 100169. https://doi.org/10.1016/j.paerosci.2020.100619 2. State-of-the-Art Small Spacecraft Technology, NASA/TP−20260003140. URL: https://www.nasa.gov 2026/05soa-2026. (Last accessed on February 18, 2026). 3. Peng Zheng, Jianjun Wu, Yu Zhang. A comprehensive review of atmosphere breathing electric propulsion. International Journal of Aerospace Engineering. 2020. Art. 8811847. 21 pages. https://doi.org/10.1155/2020/8811847 4. Hsu Andrea, Dragnea Horatiu, Schilling John 2223. Small Satellite Propulsion Technologies. Compendium The Aerospace Corporation, DISTRO A, Version 1.41. DISTRO A: Approved for public release. OTR-2024-00338. URL: https://aerospace.org/sites/default/files/2024-02/20231218%20Small%20Satellite%20Propulsion%20Survey_DISTRO_A.pdf (Last accessed on February 18, 2026). 5. Goebel D. M., Katz I., Mikellides I. G. Fundamentals of Electric Propulsion: Ion and Hall Thrusters. Jet Propulsion Lab. California Institute of Technology. March 2008. 486 pp. URL: https://descanso.jpl.nasa.gov/SciTechBook/series1/Goebel__cmprsd_opt.pdf (Last accessed on February 18, 2026).https://doi.org/10.1002/9780470436448 6. Navarro-Cavalle J., Wijnen M., Fajardo P. Ahedo E.. Development and characterization of the helicon plasma thruster prototype HPT05M. 36th International Electric Propulsion Conference. Vienna. Austria. September 15-20, 2019. URL: https://ep2.uc3m.es/assets/docs/pubs/conference_proceedings/nava19.pdf (Last accessed on February 18, 2026). 7. Giannetti V., Ferrato E., Andreussi T. On the critical parameters for feasibility and advantage of air-breathing electric propulsion systems. Acta Astronautica. 2024. V. 220. P. 345-355. https://doi.org/10.1016/j.actaastro.2024.04.042 8. Reinhard P., Neumann C. Centre-Triggered Pulsed Cathodic Arc Spacecraft Propulsion. URL:http://hdl.handle.net/2123/13810 (Last accessed on February 18, 2026). 9. Aksenov I. I. et al. Vacuum Arc: Plasma Sources, Coating Deposition, and Surface Modification. Kyiv: Naukova Dumka, 2012. 727 pp. (In Russian). 10. Mesyats G. A. Ecton or electron avalanche from metal. Physics-Uspekhi. 1995. V. 38. No. 6. Pp. 567- 590.https://doi.org/10.3367/UFNr.0165.199506a.0601 11. Duppada Guru Sankar, Taploo Anmol, Soni Vikas, Karp Adam, Spinelli Jake, Keidar Michael. Side feeding mechanism for micro cathode arc thruster. Journal of Electric Propulsion. 2025. V. 4. Art. 16 (2025). https://doi.org/10.2514/6.2025-2385 12. Merino M. Ahedo E. Magnetic nozzles for space plasma thrusters. Encyclopedia of Plasma Technology. 2016. URL: https://www.taylorfrancis.com/books/e/9781351204958/chapters/10.10 (Last accessed on February 18, 2026). 13. Kuzmichev A. I. Magnetron Sputtering Systems. Kyiv: Avers, 2008, 244 pp. (In Russian). 14. Anders André High Power Impulse Magnetron Sputtering: A journey from early research, Encyclopedia of Plasma Technology - Two Volume Set, eBook ISBN9781351204958 Guðmundsson J. T. аt al AVS Seminar - Plasma Applications Group Santa Clara, CA. 2011. May 12. URL: https://nccavs-usergroups.avs.org/wp-content/uploads/PAG2011/2011_5anders.pdf (Last accessed on February 18, 2026). 15. Anders Andre, Andersson J. Gasless sputtering: Opportunities for ultraclean metallization, coatings in space, and propulsion. Appl. Phys. Lett. 2008. V. 92. Art. 221503. https://doi.org/10.1063/1.2938414 16. Gryshkevych A. D., Khitko A. V. Using a plasma electron source in a magnetron ion sputtering system. Problems in High-Temperature Engineering. 2011. Pp. 42-45. (In Russian). 17. Tiron V., Velicu I-L. Understanding the ion acceleration mechanism in bipolar HiPIMS: the role of the double Layer structure developed in the after-glow plasma. Plasma Sources Science and Technology. 2020. V. 29. No. 1. Art. 015003. https://doi.org/10.1088/1361-6595/ab6156 18. Avino F. at al. After-glow dynamics of plasma potential in bipolar HiPIMS discharges. Plasma Sources Sci. Technol. 2021. V. 30. Art. 115015. https://doi.org/10.1088/1361-6595/ac2aed 19. Yang Luo, Mingyue Han, Duoduo Li, Ling Tang et al. Plasma potential and ion energy characteristics in BP-HiPIMS discharge with double layer. Plasma Sources Science and Technology. 2024. V. 33. Art. 105007. https://doi.org/10.1088/1361-6595/ad52bf 20. Gryshkevych O. D., Hryniuk S. I. Magnetron formation and use of intensive gas-metal plasma flows. Teh. Meh. 2019. No. 2. Pp. 102-113. (In Russian). https://doi.org/10.15407/itm2019.02.102 21. Gryshkevych O. D., Hryniuk S. I. Development and study of a prototype low-frequency power source for a high-current pulsed magnetron discharge. Teh. Meh. 2019. No. 4. Pp. 137-147. (In Russian). https://doi.org/10.15407/itm2019.04.137 22. . Raizer Yu. P. Fundamentals of the Modern Physics of Gas-Discharge Processes. Moscow: Nauka, 1980. 415 pp. (In Russian).
PROSPECTS FOR THE IMPLEMENTATION OF ERP SYSTEMS AND MODULAR ARCHITECTURE IN SPACE ENTERPRISE MANAGEMENT
DOI: https://doi.org/10.15407/itm2026.02.062 Automated management systems, ERP decisions, and various corporate information platforms are becoming increasingly popular both within Ukraine and on the global market. Such innovations form a basis for process modernization, ensuring the integration and coordination of all key enterprise functions. A modern ERP system is not limited to the automation of everyday and routine operations, such as material cost accounting, stock control, or document flow. It includes a wider set of tools aimed at strategic planning, predictive analytics and making complex management decisions. The implementation of such a system is an important marker of the enterprise's transition to a qualitatively new level of organizational development. Thanks to the use of this tool, the enterprise gets the opportunity not only to harmonize all aspects of its work, but also to maximally fulfil its potential through more effective resource management, production process optimization, and increased competitiveness. This, in its turn, allows the enterprise to adapt to rapid market changes and occupy leading positions in the chosen industry. Digital technologies are rapidly becoming a basis for space industry development, opening up new opportunities for the design, production, testing, and operation of spacecraft and rocket systems. This work explores both the theoretical aspects and the practical application of ideas on rocketry enterprise management. Particular attention is paid to the role of digital platforms, ERP systems, automated management decisions, and modular architecture in creating a unified integrated information environment. A concept of a multi-level management model is developed, which contributes to resource integration, enhancement of data processing efficiency, and management process optimization in real time. The implementation of such a concept opens up the possibility of significantly reducing computational burden in real time, which, in its turn, contributes to increasing the reliability of the entire complex of computing systems. This implementation not only optimizes the operation of the technical infrastructure, but also significantly simplifies the process of making management decisions, providing managers with access to timely, high-quality, structured and comparable information. This approach ensures that all data will have a practical value and will be maximally focused on management needs. REFERENCES 1. Wörner J. Space 4.0 European Space Agency. URL: https://www.esa.int/About_Us/Digital_Agenda/Space_4.0_for_ESA. (Last accessed on May 4, 2026). 2. The Space Economy in Figures. OECD iLibrary. 2024. URL: https://www.oecd.org/en/publications/the-space-economy-in-figures_c09d3f71-en.html. (Last accessed on May 4, 2026). 3. Alpatov A. P., Marchenko V. T., Khorolskiy A. P., Sazina N. P. The status and directions for improving the regulatory and procedural framework for the rocket and space technology development in Ukraine. Science and Innovation. 2022. V. 18. No. 1. Pp. 76-88. (In Ukrainian). 4. Danylovych-Kropyvnytska M., Bashak P. Problems of the aviation and space industry as part of the defense-industrial complex of Ukraine. Scientific Works of Interregional Academy of Personnel Management. Political Sciences and Public Management. 2022. No. 2 (62). Pp. 60-65. (In Ukrainian). 5. Skoruk O., Grudzevych Yu. Integration of digital technologies and economic and mathematical modeling in business processes of enterprises. Digital Economy and Economic Security. 2024. No. 6 (15). Pp. 81-85. (In Ukrainian). 6. Popivniak Yu. ERP systems in electronic commerce: accounting aspects. Digital Economy and Economic Security. 2025. No. 6 (21). Pp. 324-330. (In Ukrainian). 7. Zavrazhnyi K. Yu., Kulyk A. K., Sokolov M. A. Analysis of implementation the ERP-system for achieving sustainable enterprise development in the context of digital transformation. Mechanism of Economic Regulation. 2024. No. 2 (104). Pp. 33-41. (In Ukrainian). https://doi.org/10.32782/mer.2024.104.04 8. Zavadskyi I. O. Fundamentals of Databases. Kyiv: PP I. O. Zavadskyi, 2011. 192 pp. (In Ukrainian). 9. Dotsenko S. I. Database Management Organization and Systems. Kharkiv: Ukrainian State University of Railway Transport, 2023. 117 pp. (In Ukrainian).
DEVELOPMENT AND CHARACTERIZATION OF A METAL PLASMA VACUUM-ARC THRUSTER
DOI: https://doi.org/10.15407/itm2026.02.069 Metal plasma vacuum-arc thrusters attract increased attention due to their design simplicity, easy scalability, and stable, reliable operation. The goal of this work is to develop and characterize an electric metal plasma vacuum-arc thruster with a long service life. Research methods: a bibliographic analysis of the scientific and technical literature, a gravimetric thrust measurement method, and measurement of electrical characteristics. The article presents the results of development and characterization of a metal plasma vacuum-arc thruster with a disk cathode made of aluminum alloy 5056 (analog of AMG6 alloy). The metal plasma thruster is a new class of electric propulsion systems in which the cathode metal is converted into plasma using an electric dischargeб, and the accelerated flow of the metal plasma produces jet thrust. Compared with known designs of metal plasma vacuum-arc thrusters, the thruster developed has a significant cathode mass (805 g) with a working surface area of 298 cm2. The thruster has a special magnetic system to control cathode spot motion over the working surface of the cathode. Cathode spot motion was studied at different magnetic field magnitudes and configurations, and the thrust was determined at different values ​​of the discharge current and compared with that of existing metal plasma vacuum-arc thrusters. The scientific novelty of the work lies in that the electric vacuum-arc thruster developed is the first to use the controlled motion of cathode spots in order to ensure uniform erosion of the cathode material and extend the service life. A disk cathode and cathode spot motion control by the magnetic field of a solenoid and a permanent magnet are a novelty too. The practical value of the work lies in recommendations on the engineering design of electric metal plasma thrusters and in the results of characterization of an electric thruster with a disk cathode. The article is intended for experts in rocket propulsion engineering. REFERENCES 1. O'Reilly D., Herdrich G., Kavanagh D.F. Electric propulsion methods for small satellites: a review. Aerospace. 2021. V. 8. No. 1. Art. 22. https://doi.org/10.3390/aerospace8010022 2. Kolbeck J., Anders A., Beilis II, Keidar M. Micro-propulsion based on vacuum arcs. J. Appl. Phys. 2019. V.125. Iss. 22. Art. 220902. https://doi.org/10.1063/1.5081096 3. Pietzka M. Development and Characterization of a Propulsion System for CubeSats Based on Vacuum Arc Thrusters. Ph.D. Thesis, University of the Bundeswehr Munich, Munich, Germany, 2016. 177 pp. 4. Polk J. E., Sekerak M. J., Ziemer J. K., Schein J., Anders A. A Theoretical analysis of vacuum arc thruster and vacuum arc ion thruster performance. IEEE Trans. Plasma Sci. 2008. V. 36. No. 5, Pp. 2167-2179. https://doi.org/10.1109/TPS.2008.2004374 5. Krishnan M., Velas K., Leemans S. Metal plasma thruster for small satellites. AIAA Journal. 2020. V. 36. No. 4. Pp. 535-539. https://doi.org/10.2514/1.B37603 6. Anders A. Cathodic Arcs: From Fractal Spots to Energetic Condensation. New York: Springer Science Business Media, 2008. 540 pp. https://doi.org/10.1007/978-0-387-79108-1 7. Lun J. Performance Improvement of Vacuum Arc Thrusters. A thesis submitted to the Faculty of Engineering and the Built Environment at the University of the Witwatersrand, Johannesburg, in fulfilment of the requirements for the degree of Doctor of Philosophy. 2015. 270 pp. 8. Marvin Kühn M., Schein J. Development of a high-reliability vacuum arc thruster system. Journal of Propulsion and Power. 2022. V. 38. No 5. Pp. 752-758. https://doi.org/10.2514/1.B38202 9. Duppada G. S., Taploo A., Spinelli J., Keidar M. Toward achieving longevity of micro cathode thrusters. J. Appl. Phys. 2025. Vol. 138. No. 2. Art. 023302.https://doi.org/10.1063/5.0273158 10. Schein J., Qi N., Binder R., Krishnan M., Ziemer J. K., Polk J. E., Anders A. Inductive energy storage driven vacuum arc thruster. Review of Scientific Instruments. 2022. V. 73. No. 2. Pp. 925-927. https://doi.org/10.1063/1.1428784 11. Spirin Ye. V., Nadtoka V. M. Electric thrusters utilizing metal plasma. Space Technology. Missile Armaments. 2025. Iss. 2. Pp.24-34. (In Ukrainian). https://doi.org/10.33136/stma2025.02.024 12. Frankovich, J. K., Krishnan, M., Mackey, J. et al. Qualification of a pulsed, millinewton class metal plasma thruster for broad mission applications. J. Electr. Propuls. 2025. Vol. 4. Art. 65. https://doi.org/10.1007/s44205-025-00139-9 13. Frankovich K., Krishnan M. Metal plasma thruster (MPT): from garage to orbit in 4 years. 3AF Space Propulsion Conference in Glasgow, Scotland, 20 - 23 May 2024 14. Krishnan M, Frankovich J. K., Mackey J. Impulse bit measurements from metal plasma thruster. Journal of Propulsion and Power. 2021. V. 37. No. 4. Pp. 577-583. https://doi.org/10.2514/1.B38191 15. Sethuraman S. K., Barrault М. R. Study of the motion of vacuum arcs in high magnetic field. Journal of Nuclear Materials. 1980. V. 93-94. Pp. 791-798. https://doi.org/10.1016/0022-3115(80)90209-3 16. Dukhopelnikov D.V., Kirillov D.V., Ryazanov V.A., Naing Kyaw Win. Optimization of the cathode spot trajectory to improve the uniformity of cathode production in a vacuum arc evaporator. Engineering Journal: Science and Innovation. 2013. V. 10. URL: http://engjournal.ru/catalog/machin/plasma/1042.html (Last accessed on November19, 2013). 17. Spirin Ye. V. Electroreactive low-thrust jet engine with electric arc discharge. XXV International Conference "Man and Space": Abstracts of the XXV International Youth Scientific and Practical Conference "Man and Space", Dnipro, April 12-14, 2023. 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EFFECT OF THE TEMPERATURE ON THE PARAMETERS OF CAPILLARY PROPELLANT MANAGEMENT DEVICES
DOI: https://doi.org/10.15407/itm2026.02.079 This work is devoted to the study of the effect of propellant component temperature oscillations in orbital flight on the main design parameters of capillary propellant management devices. The presence of these devices in the propellant feed system of multi-purpose spacecraft is associated with the requirements of sustainer engine restarts in near-zero-gravity conditions. In zero gravity, a liquid propellant is mixed in an arbitrary manner with the pressurant gas, thus causing the danger of the gas phase entering the feed line and then the engine combustion chamber, which, in turn, may lead to a start failure. To avoid this emergency situation, various propellant management devices have been developed and successfully used over the past several decades, among which the most common and universal ones are those based on capillary forces. Despite a number of significant advantages in comparison with other devices, capillary ones have some drawbacks that are associated with the features of capillary forces. In particular, the temperature of any propellant affects its physical properties, thus affecting the performance of capillary propellant management devices. The goal of this work was to identify the effect of propellant temperature oscillations on the performance of these devices. The static and dynamic holding capacities of capillary propellant management devices, which are their main critical design parameters, were calculated for propellant temperatures higher than the design temperature. The temperature dependence of the surface tension coefficient, the dynamic viscosity coefficient, and the liquid propellant density was taken into account. The results obtained show that the operability of capillary propellant management devices in orbital flight deteriorates due to a local increase in propellant temperature in a certain part of the tank. For a reliable engine restart, it is necessary to ensure a sufficiently high operability reserve factor of these devices. In addition, it is advisable to take measures to reduce a local increase in propellant temperature in the tanks in zero gravity. The use of the results in engineering practice allows one to predict the design parameters of propellant management devices at the draft design stage of promising multi-purpose spacecraft. REFERENCES 1. Belyaev N. M. Design of Rocket Pneumohydraulic Systems. Moscow: Mashinostroyeniye, 1983. 219 pp. (In Russian). 2. Babyichuk Ya. O., Nazarenko D. S., Siedykh I. V. Calculation and experiment method to study propellant settlement in a tank before sustainer engine restarts. Teh. Meh. 2019. No. 2. Pp. 3 - 47. (In Russian). https://doi.org/10.15407/itm2019.02.039 3. Kozlov A. A., Novikov V. N., Solov'ev E. V. А.А. Feed and Control Systems of Liquid-Propellant Rocket Systems. Moscow: Mashinostroyeniye, 1988. 352 pp. (In Russian). 4. Bagrov V. V., Kurpatenkov A. V., Polyaev V. M. et al. Capillary Systems for Liquid Withdrawal from Spacecraft Tanks. V. M. Polyaev (Ed.). Moscow: ENERGOMASh, 1997. 328 pp. (In Russian). 5. Ono S., Kondo S. Molecular Theory of Surface Tension in Liquids. Moscow: Foreign Literature Publishers, 1983. 254 pp. (In Russian). 6. Davydov S. A. Experimental studies of the effect of the elastic coefficient of grid phase separators on their holding capacity. Journal of Rocket-Space Technology. 2004. Iss. 8. No. 12. Pp. 11-17. (In Russian). 7. Regnier W.W., Hess D.A. Design and development of a passive propellant management system. J. of Spacecraft and Rockets. 1978. V.15. No. 5. Pp. 299-304. https://doi.org/10.2514/3.57320 8. Davydov S. A., Makarova A. S. Experimental assessment of the effect of a varying pressure on gas break through a metal grid. Deposited in the All-Union Institute of Scientific and Technical Information. No. 26 -19 - V89 - 1989. 11 pp. (In Russian). 9. Tegart J.R. Influence of pressure transients on the performance of capillary propellant acquisition systems. AIAA Paper. 1976. No. 597. 8 pp. https://doi.org/10.2514/6.1976-597 10. Sichevoi A. V., Davydov S. A., Gorelova K. V. Dynamic loading coefficient of grid propellant management devices. In: System Design and Characteristic Analysis of Aerospace Hardware. V. X. Dnipropetrovsk, Porogi, 2010. Pp. 106 -113. (In Russian). 11. Vargaftik N. B. Handbook on the Thermophysical Properties of Gases and Liquids. Moscow: Nauka, 1972. 720 pp. (In Russian). 12. Frolov Yu. G. Colloidal Chemistry Course: Surface Phenomena and Disperse Systems. Moscow: Al'yans, 2014. 464 pp. (In Russian).