Technical Mechanics
type: channel
description: 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, dow…
publisher: текст 3
language: en-US
publication name: Technical Mechanics
items: FEATURES OF THE AERODYNAMIC OPTIMIZATION OF THE SPATIAL SHAPE OF AXIAL-FLOW COMPRESSOR BLADES
items: AEROSTATIC SYSTEMS IN DEFENSE APPLICATIONS: THE CURRENT CHALLENGES AND THE STATE OF THE ART
items: DEPLOYMENT OF THE ROTATING TWO BODIES TETHER IN AN ORBIT
items: ANALYSIS OF THE MAGNETIC FIELD AND THE MAGNETIC FLUX IN SPACECRAFT’S PASSIVE DEORBIT SYSTEMS
items: ELECTROJET THRUSTER TO BALANCE AN AERODYNAMIC DRAG ON A SMALL SPACECRAFT IN A VERY LOW EARTH ORBIT
items: PROSPECTS FOR THE IMPLEMENTATION OF ERP SYSTEMS AND MODULAR ARCHITECTURE IN SPACE ENTERPRISE MANAGEMENT
items: DEVELOPMENT AND CHARACTERIZATION OF A METAL PLASMA VACUUM-ARC THRUSTER
items: EFFECT OF THE TEMPERATURE ON THE PARAMETERS OF CAPILLARY PROPELLANT MANAGEMENT DEVICES
items: ANALYSIS OF THE STRAIN OF A SUBSOILER CHAIN LINK AND ITS FORMING BEHAVIOR UNDER STATIC LOADING
items: MATHEMATICAL SIMULATION OF THE STRESS AND STRAIN FIELD OF HIP JOINT ELEMENTS UNDER STATIC LOADS AT DIFFERENT STAGES AFTER A TOTAL HIP ARTHROPLASTY

FEATURES OF THE AERODYNAMIC OPTIMIZATION OF THE SPATIAL SHAPE OF AXIAL-FLOW COMPRESSOR BLADES
type: item
description: 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. …
creator: Yu. O. KVASHA
creator: N. A. ZINEVYCH
creator: N. V. PETRUSHENKO
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 3
ending page: 9

AEROSTATIC SYSTEMS IN DEFENSE APPLICATIONS: THE CURRENT CHALLENGES AND THE STATE OF THE ART
type: item
description: 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.p…
creator: V. K. SHAMAKHANOV
creator: B. I. TEROKHIN
creator: E. O. LAPKHANOV
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 10
ending page: 22

DEPLOYMENT OF THE ROTATING TWO BODIES TETHER IN AN ORBIT
type: item
description: 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., Kho…
creator: Ch. WANG
creator: O. E. ZAKRZHEVSKYI
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 23
ending page: 37

ANALYSIS OF THE MAGNETIC FIELD AND THE MAGNETIC FLUX IN SPACECRAFT’S PASSIVE DEORBIT SYSTEMS
type: item
description: 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 ef…
creator: B. V. YURKOV
creator: S. Yu. ASMOLOVSKYI
creator: S. M. KULAHIN
creator: M. P. RIZNYCHENKO
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 38
ending page: 48

ELECTROJET THRUSTER TO BALANCE AN AERODYNAMIC DRAG ON A SMALL SPACECRAFT IN A VERY LOW EARTH ORBIT
type: item
description: 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 conceptu…
creator: O. D. GRYSHKEVYCH
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 49
ending page: 61

PROSPECTS FOR THE IMPLEMENTATION OF ERP SYSTEMS AND MODULAR ARCHITECTURE IN SPACE ENTERPRISE MANAGEMENT
type: item
description: 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 …
creator: I. O. HUSAROVA
creator: D. V. KLYMENKO
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 62
ending page: 68

DEVELOPMENT AND CHARACTERIZATION OF A METAL PLASMA VACUUM-ARC THRUSTER
type: item
description: 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. REF…
creator: Ye. V. SPIRIN
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 69
ending page: 78

EFFECT OF THE TEMPERATURE ON THE PARAMETERS OF CAPILLARY PROPELLANT MANAGEMENT DEVICES
type: item
description: 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 a…
creator: S.O. DAVYDOV
creator: M.O. KATRENKO
creator: N.S. PRYADKO
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 79
ending page: 87

ANALYSIS OF THE STRAIN OF A SUBSOILER CHAIN LINK AND ITS FORMING BEHAVIOR UNDER STATIC LOADING
type: item
description: 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 . 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. She…
creator: B. A. SHELUDCHENKO
creator: Ye. S. SYROID
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 88
ending page: 97

MATHEMATICAL SIMULATION OF THE STRESS AND STRAIN FIELD OF HIP JOINT ELEMENTS UNDER STATIC LOADS AT DIFFERENT STAGES AFTER A TOTAL HIP ARTHROPLASTY
type: item
description: 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 acetabu…
creator: D. V. HOROBETS
creator: M. B. SOBOLEVSKA
creator: O. Ye. LOSKUTOV
rights: Copyright (c) 2026 Technical Mechanics
date: 2026-07-02
publication date: 2026-07-02
number: 2
starting page: 98
ending page: 110