The development of modern aviation technology imposes special requirements on its operational characteristics, such as strength, rigidity, durability, as well as maintainability. The specifics of aviation technology is the use of low-rigid parts, mainly airframe panels. Most often they are connected to the frame of the structure using rivets and bolts, which are stress concentrators. Also, there are frequent cases of damage to panels in operation in the area of fixing points, such as dents, nicks, cracks and other defects. Their presence reduces the service life of the entire product. In this regard, from the point of view of restoring the operability (repair) of such prefabricated structures, several methods are implemented in practice. One of their variants of which is the use of a bougie, which is a special connecting structure of the bushing type. This design makes it possible to perform the presented repairs cost-effectively and efficiently.

The installation of the bougie, traditionally, was considered only from the point of view of the possibility of its pressing into the skin and the frame part. The controlled parameter, in this case, was the contact force that occurs when installing parts with tension. At the same time, there is currently no reliable data on the effect of the bush on the static and fatigue strength of the structure as a whole.

The presented work is devoted to determining the influence of the installation of the bush on the prefabricated structure. The study was carried out using the finite element method and solving the problem of the theory of a deformed solid. In particular, the influence of various parameters (the amount of tension, the value of the live jumper, the radius of the bush, etc.) on the stress concentration coefficients is considered. Based on the numerical experiment, recommendations for the installation of bushes are given.

Keywords: theory of a solid deformed body, contact problem, bush, fatigue strength, theoretical concentration coefficient.

Mikhail Yu. Ryzhkov (Irkutsk, Russian Federation) – Mechanical Engineer, Department of the Strength Calculations, PJSC Corporation "Irkutsk", PhD student, Irkutsk National Research Technical University (Irkutsk, 664074, Lermontov str., 84, e–mail: mixa1997ruz@mail.ru).

Anatoly A. Pykhalov (Irkutsk, Russian Federation) – Doctor of Technical Sciences, professor, Director, Educational and Scientific Center "Computer Technologies of Engineering Analysis", Professor of the Department "Physics, Mechanics and Instrumentation", Irkutsk State Transport University; Professor of the Department "Mechanics and Resistance of Materials", Irkutsk National Research Technical University (Irkutsk, 664074, Lermontov str., 84, e-mail: pykhalov_aa@mail.ru).

Mikhail S. Yakhnenko (Irkutsk, Russian Federation) – CSc in Technical Sciences, Design engineer of the Department of Strength Calculations, PJSC Corporation "Irkutsk" (Irkutsk, 6640204, Novatorov str., 3,
e-mail: holtfor@mail.ru).

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The processes in the dissociation zone during the combustion of aluminum particles in the medium "79 % He + 21 % O2" are analyzed. The necessity of taking into account the effect of pressure on oxygen dissociation to explain the influence of physical processes on the rate of combustion of particles and on the size of oxide particles, in particular on the conditions for the formation of ultrafine oxide in the medium "79 % He + 21 % O2" is substantiated. The calculations were performed for the conditions of quasi-stationarity and spherical symmetry of processes in the pre-flame region, for particles with a diameter of 220 μm and ambient pressure p = 1–6 MPa in accordance with the results of experiment. The separation of the pre-flame region with the inclusion of a dissociation zone in it is proposed. It has been established that the values of the concentration of the dissociating oxidizer at the flame boundary at high pressure decrease by 10 times compared to atmospheric pressure, and the temperature rises by 15 %. The distributions of the concentrations of oxidizing components, the temperature of the medium depending on the ratio of the R coordinates of the internal points of the region to the current radius of the particle R0, the coordinates of the points of the flame boundary and the concentration of the oxidizer on them depending on the pressure of the medium are obtained. It is shown that the dissociation zone lies within 1.6 £ R/R0 £ 2.9 for combustion at a pressure of p = 6 MPa, and within 2.0 £ R/R0 £ 4.0 at atmospheric pressure. The results of the analysis suggest that due to a further decrease in the relative concentration of the oxidizer in the flame zone, the oxidizer does not enter the surface of the particle, which explains the absence of coarse oxide during the combustion of aluminum particles in the medium "79 % He + 21 % O2".

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Aleksey Yu. Kryukov (Perm, Russian Federation) – Ph. D. in Technical Sciences, Assistant Professor, Department of Machine Engineering Innovation Technologies, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, e-mail: alexkryukov@list.ru).

Vladimir I. Malinin (Perm, Russian Federation) – Doctor of Technical Sciences, Professor, Department of Rocket and Space Engineering and Power Generating Systems, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, e-mail: malininvi@mail.ru).

Arsen A. Nadyrov (Perm, Russian Federation) – Student, Department of Rocket and Space Engineering and Power Generating Systems, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, e-mail: arseseninsin@gmail.com).

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In modern aerospace technology, including aircraft engine construction, polymer composite materials are widely used. The active introduction of such materials is due to strength comparable to metals at a significantly lower density, which is especially important in the aerospace industry. PCMs are used in critical products that may be subject to fatigue failure. Designing products from layered polymer composite materials implies the possibility of choosing the laying of layers. Each new combination of these layers requires various expensive strength studies, including fatigue tests.

The article presents the results of an experimental study of the patterns of thermal behavior of L-shaped flanges of a typical aircraft structure made of polymer composite materials at different stages of fatigue failure. The study of the thermal state of a product at different stages of fatigue failure is an important stage in the study of fatigue characteristics. The relevance of such a technique is justified by the need to reduce the cost of testing compared to expensive classical techniques.

According to the results of the research, two types of destruction were identified. The main type of failure is delamination between the body element and the flange element. In some samples, cracks appeared in the L-shaped flange element at different stages of fatigue failure.

It was determined that during fatigue failure, at certain operating times, stabilization of the heat release process is observed. A shift of the heating zone towards the embedment with fatigue life was revealed, which indicates the development of damage in this area. The results obtained indicate that the heating zone of the sample corresponds to the position of the fatigue crack tip and it is displaced along the sample in the process of increasing delamination.

Keywords: polymer composite materials, laminated carbon fiber, flange, high-cycle fatigue, damage accumulation, thermography, fatigue curve, experimental mechanics, thermography, fatigue failure.

Danil G. Solomonov (Perm, Russian Federation) – PhD Student, Department of Aviation Engines, Perm National Research Polytechnic University (93, Komsomolsky аv., 614990, Perm, e-mail: solomonov1198@yandex.ru).

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The article is devoted to the analysis of various compositions of granular solid propellant for use in a ramjet. The disadvantages of existing types of propellant, such as powdered metal, liquid, solid ones, are given. The main advantages of the new propellant type are revealed. A structural and layout scheme of a ramjet on granular solid propellant is proposed and desribed; the scheme of a granular solid propellant rocket engine is taken as a basis. The mastered and promising high-enthalpy components for granular propellant have been selected. Thermodynamic calculations of their combustion processes in the combustion chamber of the gas generator and afterburning in the afterburner are carried out (propellant components mass fractions and air and propellant mass flow ratio were varied). The ranges of changes in the main parameters are established both in the gas generator (temperature, propellant density, k-phase content) and the entire ramjet as a whole (the ratio of air and propellant consumption, afterburning temperature, specific impulse). During the analysis of the results of thermodynamic calculations of granular propellant compositions the most preferable mastered composition was established and the criteria for the efficiency of the granular propellant ramjet were formulated. The analysis shows the advantages and disadvantages of promising components application in relation to the mastered components application. The result of the study is the possibility of using granular propellant in ramjets of multiple on-off for high-altitude aircraft (flight altitude over 30 km). The high flight altitude and repeated switching on and off of the engine will increase its flight range and reduce the amount of fuel required.

Keywords: jet, granular solid propellant, ramjet, thermodynamic calculation, gas generator, afterburner, engine efficiency criteria, k-phase mass fraction, specific impulse, air and propellant mass flow ratio, octogen, azepines.

Grigory A. Dotkin (Perm, Russian Federation) – PhD Student, Department of Rocket and Space Engineering and Power Generating Systems, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, e-mail: g.dotkin@gmail.com).

Maksim D. Zorin (Perm, Russian Federation) – PhD Student, Department of Rocket and Space Engineering and Power Generating Systems, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, e-mail: macy-1998@mail.ru).

Vladimir I. Malinin (Perm, Russian Federation) – Doctor of Technical Sciences, Professor, Department of Rocket and Space Engineering and Power Generating Systems, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, e-mail: malininvi@mail.ru).

1. Malinin V.I. Vnutrikamernyye protsessy v ustanovkakh na poroshkoobraznykh metallicheskikh goryuchikh [Intra-chamber processes in installations on powdered metallic fuels]. Yekaterinburg – Perm: Ural branch of RAS, 2006.

2. Yagodnikov D.A. Goreniye poroshkoobraznykh metallov v gazodispersnykh sredakh [Combustion of powdered metals in gas dispersed media]. Moscow: MSTU named after N.E. Bauman, 2018, 446 p.

3. Zemerev E.S. Kriticheskoye istecheniye sypuchikh materialov v pnevmotransportnoy sisteme podachi poroshka [Critical outflow of bulk materials in a pneumatic conveying system for feeding powders]: PhD Diss. – Perm: PSTU, 2017, 116 p.

4. Konstruktsiya i proyektirovaniye kombinirovannykh raketnykh dvigateley na tverdom toplive: uchebnik [Constrution and design of combined solid-fuel rocket engines]. B.V. Obnosov, V.A. Sorokin, L.S. Yanovskiy and others. – Moscow: Bauman MSTU Publ., 2012. – 303 p.

5. Yel′kin A.V., Malinin V.I. Raketnyy dvigatel na granulirovannom tverdom toplive [Rocket engine on granular solid fuel]. Aerokosmicheskaya tekhnika, vysokiye tekhnologii i inovatsii. – 2019. – Vol. 2. – P. 65-68.

6. A.V. Yel′kin, E.S. Zemerev, V.I. Malinin and others. Raketnyy dvigatel na granulirovannom tverdom toplive [Rocket engine on granular solid fuel]. PNRPU Aerospace Engineering Bulletin, 2021, no. 64, pp. 16-24.

7. Yelkin, A.V. Raketnyye dvigateli dlya kosmicheskikh letatel′nykh apparatov na psevdoozhizhennykh tverdykh toplivakh [Rocket engines for spacecraft on fluidized solid propellants, their design and thermodynamics]. Teplovyye protsessy v tekhnike, 2021, Vol. 13, no. 11, p. 509-518.

8. Dotkin G.A., Zorin M.D. Raketno-pryamotochnyy dvigatel′ na granulirovannom tverdom toplive [Granular propellant scramjet]. Collection of abstracts of the international youth scientific conference XLIX “Gagarinskiye chteniya 2023”, Moscow: «Pero», 2023, pp. 108-109.

9. Belov G.V., Trusov B.G. Termodinamicheskoye modelirovaniye khimicheski reagiruyushchikh system [Thermodynamic modeling of chemically reacting systems]. Moscow: Bauman MSTU Publ., 2013, 96 p

10. Rogov, N.G. Smesevyye raketnyye tverdyye topliva: Komponenty. Trebovaniya. Svoystva: ucheb. Posobiye [Mixed rocket solid propellants. Components. Requirements. Properties: tutorial]. SPb.: SPbSIT, 2005, 195 p.

11. D.B. Lempert, A.I. Kazakov, G.V. Shilov, E.L. Ignat′yeva, A.I. Stepanov, D.V. Dashko, A.V. Nabatova, p.M. Aldoshin. Allilzameshchennyye furazanoazepinov. Struktura, entalpiya obrazovaniya, ballisticheskaya effektivnost, termostabilnost [Allil-substituted furazanazepines. Structure, formation enthalpy, ballistic efficiency, thermical stability.]. Tezisy XVI Vserossiyskogo simpoziuma po goreniyu i vzryvu 2022, p. 56-57.

12. L.S. Yanovsky, D.B. Lempert, V.V. Raznoschikov, I.S. Averkov. Otsenka effektivnosti tverdykh topliv na osnove vysokoentalpiynykh dispergatorov dlya raketno-pryamotochnykh dvigateley [Scramjet solid fuel based on high enthalpy dispersants efficiencty evaluation]. Zhurnal prikladnoy khimii, 2019, Vol. 92, No. 3, p. 322‑342.

13. A.F. Zholudev, M.B. Kislov, I. P. Averkov [i dr.]. Features of combustion of gas-generating solid compositions based on high-enthalpy dispersants. Russian Chemical Bulletin, International Edition, 2021, Vol. 70, No. 4, pp. 685-692.

14. I.N. Zyuzin, V.M. Volokhov, D.B. Lempert. Energeticheskiye vozmozhnosti nekotorykh proizvodnykh azofuroksanov v kachestve komponentov smesevykh tverdykh raketnykh topliv [Some azofuraxan derivatives as mixed rocket solid propellants components energy possibilities]. Khimicheskaya fizika, 2021, vol. 40, no. 9, pp. 18-26.

15. G.P. Sharnin and others. Khimiya energoyemkikh soyedineniy. Kniga 2. N–, O–nitrosoyedineniya, furoksany, furazany, azidy, diazosoyedineniya: uchebnoye posobiye [Energetic compounds chemistry. Book 2]. Kazan: KNRTU, 2011, 376 p.

Emergency hydraulic systems of indirect action with wireless control, also known as power transfer units, are widely used in systems for cleaning / releasing the landing gear of passenger aircraft. Indirect action means the conversion of hydraulic energy (power) of one of the subsystems of the aircraft using a hydraulic motor into mechanical energy to drive the pump and obtaining hydraulic energy to control the hydraulic motors involved in an emergency landing of the aircraft.

The complex nature of external influences on the operation of the hydraulic motors of the landing gear cleaning /
exhaust system in an emergency, the ambiguous characteristics of two independent circuits of the aircraft hydraulic system connected by a power transfer unit, force the development of various devices for correcting static and dynamic characteristics of the power transfer unit. When developing a corrective device of a power transfer unit designed to operate in an emergency situation, it is impractical to use devices of complex design, this is forced to abandon electronic and electromechanical correction devices.

A variant of correcting the characteristics of the emergency landing gear release drive by a pressure drop feedback device used to control the power of the power transfer units hydraulic motor is considered. Based on the new scheme of the regulator of the power transfer unit, the issues of functioning with the random nature of external influences on the hydraulic motors of the chassis cleaning/exhaust system are considered. The calculation scheme of the mathematical model of the power transfer unit is presented. A mathematical model of a power transfer unit with a pressure drop feedback device is proposed. The results of modeling a new scheme of an adjustable BMP are presented, an increase in the speed of the drive of the chassis cleaning/exhaust system, the influence of the design parameters of its devices on the operation of the regulator is shown. The characteristics of the controller, whose operation is based on the principle of sensitivity to load, the possibility of using this controller to optimize the operation of the power transfer unit, and, therefore, to increase the accuracy, stability, controllability of the entire hydraulic system of the aircraft, are presented.

Keywords: emergency hydraulic drive, power transfer unit, pump, hydraulic motor, hydraulic motor power regulator.

Nikolai A. Polyakov (Moscow, Russian Federation) – Associate Director of Design Center, Holding “Technodinamika” (p. 5, 35, Bolshaya Tatarskaya str., 115184, Moscow, e-mail: polyakovna@tdhc.ru).

Dmitry A. Kuderko (Moscow, Russian Federation) – Dr of Technical Sciences, Head of R@D center “Technodinamika” (p. 5, 35, Bolshaya Tatarskaya str., 115184, Moscow, e-mail: dm_kuderko@mail.ru).

Grigoriy K. Frolov (Ufa, Russian Federation) – Student at the Department of “Applied Hydromechanics”, Ufa University of Science and Technology (12, K. Marx str., 450008, Ufa, e-mail: kerargirit@rambler.ru).

Vladimir A. Tselischev (Ufa, Russian Federation) – Doctor of Technical Sciences, Professor, Head of Department of “Applied Hydromechanics”, Ufa University of Science and Technology (12, K. Marksa str., 450008, Ufa, e-mail: pgl.ugatu@mail.ru).

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3. N.A. Polyakov, A.A. Solovyova, Tselishchev V.A. The concept of development of power transmission units in the hydraulic system of a civil aircraft // Bulletin of PNRPU. Aerospace engineering. 2021. No. 67, pp. 5-15.

4. Polyakov N.A., Solov'yeva A.A., Tselishchev V.A. Tendentsii razvitiya gidrosistem letatelnykh apparatov [Trends in the development of hydraulic systems of aircraft]. Hydraulic machines, hydraulic drives and hydropneumoautomatics. XXV International Scientific and Technical Conference (Moscow, December 8, 2021). [Electronic resource]. Moscow: Mir Nauki, 2021, pp. 181-185.

5. Tselishchev V.A., Arefyev K.V., Mesropyan A.V., Smorodinov A.P. Analysis of jet hydraulic steering machine correction devices. PNRPU Aerospace Engineering Bulletin, 2001, issue 8, pp.15-21.

6. Tselishchev V.A. et al. Struyn·yye gidravlicheskiye rulev·yye mashiny [Jet hydraulic steering machines]. Ufa: UGATU, 2002.- 284 p.: il RNTIK "Bashtekhin-form" AN RB.

7. Tselishchev V.A., Arefyev K.V., Mesropyan A.V. Features of correction of hydraulic actuators of aircraft controls // Bulletin of UGATU, Vol.6, No. 1 (12), Ufa, Ufa State University. aviation tech. un-t, 2005, pp. 55-64.

8. Tselishchev V.A., Arefyev K.V., Mesropyan A.V. Osobennosti korrektsii gidravlicheskikh ispolnitelnykh mekhanizmov organov upravleniya letatelnykh apparatov [Identification and adaptive control of jet hydraulic steering machines]. MAI Publishing House, Moscow, 2007,282 p.

9. Kalimullin R.R., Polyakov N.A., Frolov G.K., Tselishchev V.A. Avariynyy privod vypuska shassi [Emergency landing gear release drive]. Patent for invention RU 2 780 009 C1 09/19/2022 Application: 2022101851, 01/27/2022 Published: 09/19/2022 Byul. No. 26.

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11. Modeling of swash plate axial piston pumps with conical cylinder blocks / M.K. Bahr Khalil, J. Svoboda and R.B. Bhat // Engineering Journal of Mechanical Design. Published 2004. DOI: 10.1115/1.1640363 Corpus ID: 111184657

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The implementation of the method of plasma activation of aerodynamic braking by "traces of the atmosphere" can be carried out using spacecraft for the disposal of orbital debris, created to carry out cleanup activities in near-Earth space. In this method, it is proposed to use the weak resistance of traces of the atmosphere to decelerate an artificially created large-diameter plasma formation that fills and surrounds a cloud or a single piece of space debris. The increase in the aerodynamic drag of the disposed space debris is due to orders of magnitude larger midsection of the artificial plasma formation compared to the integral area of the midsections of the CM fragments. The creation of a plasma formation is provided with the help of a gas-dust medium generator launched from a utilization spacecraft. Being subjected to ionization under the influence of outer space radiation and laser irradiation produced from a salvage spacecraft, the plasma formation “joins” the gas and dust environment with debris elements by electrostatic Coulomb forces. In addition, the authors of the article have developed a method for implementing self-ionization of an artificial plasma formation by introducing a dispersed dust additive from spontaneously emitting radionuclides into the generator medium. The values of the forces of the Coulomb interaction between the plasma medium and the surfaces of space debris objects are directly dependent on the degree of plasma ionization. To obtain a higher concentration of the ionized medium, that is, a high value of the Coulomb interaction, easily ionizing alkali and alkaline earth substances with a low ionization potential are introduced into its composition. At the same time, the Coulomb electrostatic attraction becomes able to overcome the scattering forces of the aerodynamic impact of traces of the Earth's atmosphere. Thus, the artificial plasma formation, which includes space debris, persists until reaching the dense layers of the Earth's atmosphere, where it is thermally utilized.

Keywords: artificial plasma formation, spacecraft, near-Earth space, complex technical system, own external atmosphere, finely dispersed formation.

Alexander N. Ustinov (St. Petersburg, Russian Federation) – CSc in Technical Sciences, General Director, Arsenal Machine Building Plant (1–3, Komsomola str., 195009, Saint Petersburg, e-mail: Ustinov@mzarsenal.com).

Konstantin M. Ivanov (St. Petersburg, Russian Federation) – Doctor of Technical Sciences, Professor, Rector, Baltic State Technical University "VOENMEH" named after D.F. Ustinov (1, 1st Krasnoarmeyskaya str., 190005, St. Petersburg, e-mail: bgtu@voenmeh.ru).

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When designing and upgrading existing sound-absorbing structures of an aircraft engine made of polymer composite materials, an urgent task is to identify patterns of the complex influence of design parameters of a polymer composite materials structure on its dynamic characteristics based on computational and experimental studies and the development of effective methods for establishing design design parameters from polymer composite materials, taking into account the prevention of unwanted resonant effects. The purpose of the work is to apply in practice the developed method for selecting the design parameters of tubular structures made of polymer composite materials to provide the required dynamic characteristics when designing with detuning from resonance, using the established dependences of the influence of the design parameters of a tubular structure on natural vibration frequencies. For the tubular panel of the PS-90A fan casing, a calculation model has been developed that takes into account the design heterogeneity, anisotropy of properties, design and technological parameters, fastening conditions, is acceptable in terms of computational resources and allows obtaining a validated result. Its verification was carried out by modal analysis of full-scale construction by laser vibrometry. New dependences of natural frequencies and modes of vibrations of a composite tubular structure on height, the degree of perforation of shells, the method of fastening and the prestressed state, the material and scheme of reinforcement are obtained. A calculation-experimental method has been developed for choosing the design parameters of tubular structures made of polymer composite materials according to the required resulting characteristics when designing with detuning from resonance, and the practical application of the method for a fan panel 94-05-8927 aircraft engine of the PS-90A family is shown. The conditions for the occurrence of resonant phenomena in terms of frequencies depending on the height of the structure and the mode of operation of the engine are indicated. The conclusion is made about the correctness of the previously selected design parameters of the fan panel.

Keywords: tubular structures, modal analysis, laser vibrometry, influence of design parameters on natural frequencies, design technique, design of sound-absorbing structures, detuning from resonance, composite structures, aircraft engine, calculation model.

Victor A. Efimik (Perm, Russian Federation) – CSc in Technical Sciences, Assistant, Department of Mechanics of Composite Materials and Structures, Perm National Research Polytechnical University (29, Komsomolskiy av., 614990, Perm, e-mail: v-efimik@pzmash.perm.ru).

1. Salem H., Boutchicha D., Boudjemai A. Modal analysis of the multi-shaped coupled honeycomb structures used in satellites structural design. International Journal on Interactive Design and Manufacturing, 2018, vol. 12, pp. 955–967.

2. Sakar G., Bolat F.Ç. The free vibration analysis of honeycomb sandwich beam using 3D and continuum model. International Journal of Mechanical and Mechatronics Engineering, 2015, vol. 9 № 6, pp. 1077-1081.

3. Safin A.I., Makar′yants G.M., Vyakin V.N. i dr. Modal′nyy analiz pribornoy paneli kosmicheskogo apparata [Modal analysis of a spacecraft dashboard]. Regional′naya nauchno-prakticheskaya konferentsiya, posvyashchennaya 50-letiyu pervogo poleta cheloveka v kosmos, 2011, pp. 106-108.

4. Li H., Dong B., Zhao J., Zou Z., Zhao S., Han Q., Wang Q., Wang X. Nonlinear free vibration of functionally graded fiber-reinforced composite hexagon honeycomb sandwich cylindrical shells. Engineering Structures, 2022, vol. 263, 12 p.

5. Yue S., Du Z., Shi W., Bai Y., Zou H., Zheng G. Dynamic behavior of kinetic projectile impact on honeycomb sandwich panels and multi-layer plates. Crystals, 2022, vol. 12, 17p.

6. Bendada A., Boutchicha D., Chouiter A., Miri M. Numerical-experimental characterization of honeycomb sandwich panel and numerical modal analysis of implemented delamination. Fratturaed Integrità Strutturale, 2019, vol. 49, pp. 655-665.

7. Anwar W., Khan M.Z., Israr A., Mehmood Sh., Anjum N.A. Effect of structural dynamic characteristics on fatigue and damage tolerance of aerospace grade composite materials. Aerospace Science and Technology, 2017, vol. 64, pp. 39-51.

8. Kosedag E., Ekici R. Free vibration analysis of foam-core sandwich structures. Journal of Polytechnic, 2021, vol 24 (1), pp. 69-74.

9. Jia Lou, Li Ma, Lin-Zhi Wu. Free vibration analysis of simply supported sandwich beams with lattice truss core. Materials Science and Engineering B, 2012, vol. 177, pp. 1712-1716.

10. Jia Lou, Linzhi Wu, Li Ma, Jian Xiong, Bing Wang. Effects of local damage on vibration characteristics of composite pyramidal truss core sandwich structure. Composites: Part B, 2014, vol 62, pp. 73-87.

11. Boudjemai A., Amri R., Mankour A., Salem H., Bouanane M.H., Boutchicha D. Modal analysis and testing of hexagonal honeycomb plates used for satellite structural design. Materials and Design, 2012, vol. 35, pp. 266–275.

12. Mankour A., Boudjemai A., Amri R., Salem H. Analysis of design parameter influence on the dynamic frequency response of CFFF honeycomb sandwich plate. Advanced Materials Research, 2013, vol.682, pp. 57-64.

13. Maheri M.R., Adams R.D., Hugon J. Vibration damping in sandwich panels. J Mater Sci, 2008, pp. 6604-6618.

14. Yefimik V.A., Chekalkin A.A. Modelirovaniye dinamicheskogo povedeniya konstruktsiy aviatsionnogo dvigatelya iz polimernykh kompozitsionnykh materialov s trubchatym zapolnitelem [Simulation of dynamic behavior of aircraft engine structures made of polymer composite materials with tubular filler]. PNRPU Aerokosmicheskaya Tekhnika, 2023, no. 73, P. 52-62.

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The author of the article considered issues related to the implementation of the State program of the air transport industry of the Russian Federation until 2030 for the manufacture of domestic components by years with a gradual transition of aircraft to domestic engines. The urgency of the designated problem associated with the identification of factors affecting the failure to meet the deadlines for the implementation of the order is disclosed. Theoretical and methodological provisions of project management using the concepts of lean, active production at an aircraft engine manufacturing enterprise are considered, work is described to achieve the indicators of the Lean Aerospace Initiative, including Pratt & Whitney. Taking into account the above theoretical and methodological provisions of the concepts, the paper considers the main stages in the development of the breakthrough concept of the digital twin, and identifies the main advantages and disadvantages. The analysis of the main trends in the development of the concept of the digital twin, providing strategic management of the enterprise, was carried out. In the article, within the framework of using the breakthrough concept of the digital twin, examples of foreign aviation enterprises such as Airbus, Bombardier aerospace, Boeing, Rolls Royce, Lockheed Martin Space Systems are presented. Practical examples are presented at a domestic enterprise of the implementation of the main stages of the implementation of digital technologies of JSC UEC-Aviadvigatel. An example of the development of a digital twin at the domestic enterprise PJSC "UEC-Saturn". The author of the article formulated the conclusion that in order to manage projects in order to obtain a synergistic effect, the management of the enterprise must use the described concepts together, and not separately, because using them together, the enterprise, when making objective management decisions, achieves target performance indicators, reduces time and money costs at various stages of the product life cycle in the production of aviation equipment using the advantages of modern concepts described in the article.

Keywords: lean, agile production, production and economic system, project management, aircraft engine building enterprise, digital twin concept, factors.

Aleksey G. Тashkinov (Perm, Russian Federation) – Associate Professor, Department of Economics and Management of Industrial Production, Perm National Research Polytechnic University (29, Komsomolsky аv., 614990, Perm); Head of the Coordinating Methodological Center for the Implementation of the Digital Economy, Perm Рlant "Mashinostroitel" (57, Novozvyaginskaya str., 614014, Perm, e-mail: alekss.perm@gmail.com).

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The work carried out a comprehensive experimental study of the mechanical properties in shear and torsion of 316LSi stainless steel produced using the additive manufacturing technology of wire-arc surfacing, in particular, the cold metal transfer method was used. Samples were cut from the fused on plate in horizontal and vertical directions relative to the plane of the fused layers for shear and torsion tests.

To construct strain diagrams under quasi-static loading, Instron testing systems and the digital image correlation method were used. The evolution of strain fields on surface samples in shear and torsion tests is shown. Based on the strain diagrams, the elastic, plastic and strength properties of 316LSi stainless steel were determined. It is noted that the greatest statistical scatter in the test results is observed for the shear modulus in all experiments. The results of shear and torsion tests were compared. It is shown that the elastic and plastic properties of 316LSi steel differ significantly in torsion tests and their values depend on the direction of cutting samples from the plate. It has been established that during torsion the shear modulus differs by 30 %, and the proportionality limit and conditional yield strength differ by 20 % with respect to the largest value. In shear tests, the direction of cutting samples does not significantly affect the values of similar mechanical properties.

Certain mechanical characteristics can be used to numerically simulate the processes of inelastic deformation of structural elements of complex geometry and assess the quality of selected additive manufacturing modes.

Keywords: additive manufacturing, stainless steel, experimental study, static tests, digital image correlation, shear, torsion.

Artem V. Il'inykh (Perm, Russian Federation) − PhD in Technical Sciences, Senior Researcher, Center for Experimental Mechanics, Associate Professor, Department of Experimental Mechanics and Structural Materials Science, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, е-mail: ilinih@yandex.ru).

Alexandr M. Pankov (Perm, Russian Federation) − Junior Researcher, Center for Experimental Mechanics, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, е-mail:
cem.pankov@gmail.com).

Elena M. Strungar (Perm, Russian Federation) − PhD in Physical and Mathematical Sciences, Senior Researcher, Center for Experimental Mechanics, Associate Professor, Department of Experimental Mechanics and Structural Materials Science, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, е-mail: cem.spaskova@mail.ru).

Gleb L. Permyakov (Perm, Russian Federation) − PhD in Technical Sciences, Researcher, Laboratory of Methods for Creating and Designing Material – Technology – Construction Systems, Perm National Research Polytechnic University (29, Komsomolsky av., 614990, Perm, е-mail: gleb.permyakov@yandex.ru).

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