VESTNIK of Samara University. Aerospace and Mechanical Engineering

The results of science researches, theoretical and experimental investigations are published in the journal according to the sections: Aircraft and Space Rocket Engineering; Mechanical Engineering; Information Science, Computing Technology and Control. Articles can be published in Russian or English. 
Articles in the journal are indexed by several systems: Russian Index of Science Citation (eLIBRARY.RU), DOAJRussian Science Citation Index (Web of Science), CIBERLENINKAInspecAcademic Search Ultimate (EBSCOhost), EastViewUrlich’s Periodicals DirectoryCrossRef.


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Posted: 27.08.2019
The journal “VESTNIK of Samara University. Aerospace and Mechanical Engineering” is accepted in a community-curated online directory DOAJ.


Current Issue

Vol 22, No 3 (2023)

Full Issue


Study of the efficiency of the application of gas dynamic stabilization of the flame in a current engine
Belonozhkin V.V., Teslya D.N.

An analysis of the problems that arise when dealing with issues of increasing the efficiency of using an afterburner as part of a current aircraft engine is presented, where the complex problem of reducing its influence in non-afterburning operation and improving the work process when using it is solved. In a number of cases, solving the problem comes down to a compromise which does not allow full realization of all the advantages of the design element in question. The results of a study of the influence of the method of gas-dynamic flame stabilization on the main target indicator – specific fuel consumption in a real engine are presented, which makes it possible to justify conducting this kind of research on a real object. Graphs of changes in specific fuel consumption and thrust of a gas turbine engine when changing the engine rotor speed for non-afterburning operating modes are presented, as well as graphs of changes in specific fuel consumption and thrust of a gas turbine engine when changing the speed of the aircraft for afterburning operating modes. A conclusion is drawn about the expedience of using gas-dynamic flame stabilization in the afterburner from the point of view of its effect on specific fuel consumption.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):7-12
pages 7-12 views
Digital model of the drag force of the Earth’s upper atmosphere for the design of low-orbit spacecraft
Volotsuev V.V.

A digital model is described for estimating the drag force of the Earth's upper atmosphere acting on a low-orbit spacecraft. Unlike the classical model of aerodynamic force, the digital model is the result of a computer algorithm. This algorithm calculates the field of aerodynamic force values, taking into account changes in the flight altitude, aerodynamic coefficient and the area of the spacecraft midsection over time. The calculations also use a digital model of the dynamic density of the Earth's upper atmosphere. The digital model of the drag force of the Earth's upper atmosphere is useful in the design of low-orbit spacecraft with a low-thrust jet propulsion system (thrust order – millinewtons). On the basis of the calculated values of the aerodynamic force, it is possible to form requirements for the geometry of the spacecraft, attitude modes and arrangement of low-thrust jet engines (for example, electric jet engines). With the accumulation of big data in the form of tabular functions of aerodynamic force from the space of various design and ballistic parameters of low-orbit spacecraft, it is possible to create a machine model (ML-model). It will make forecasts of the values of the design characteristics for the low-orbit spacecraft being developed according to a limited set of initial requirements.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):13-24
pages 13-24 views
Classification and comparative analysis of methods for limiting technogenic pollution in the near-Earth space
Klyushnikov V.Y., Zakharova A.P., Usovik I.V.

An analysis and classification of methods for limiting technogenic pollution of the near-Earth space according to selected criteria are presented. A brief description of existing and prospective methods for limiting technogenic pollution of the near-Earth space is given, indicating the level of technological readiness and the scope of application of a particular method.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):25-35
pages 25-35 views
Modal analysis of a spacecraft solar panel
Kryuchkov A.N., Safin A.I., Ermilov M.A., Vidyaskina A.N., Igolkin A.A., Ye. V. Shakhmatov Y.V.

The importance of analyzing free modes of mechanical oscillations of spacecraft outboard elements is due to the problem of losing their controllability because of failures in the operation of airborne guidance and navigation systems. The subject of the study is the spacecraft solar panel that represents a frame with modules with photocells attached to it. The object of the study is mechanical oscillations of such a panel as a multi-mass compliance structure. The article presents a modal analysis carried out to determine the natural frequencies and forms of vibrations of the spacecraft solar panel. A finite element model of the panel was developed. In the paper, a modal calculation was carried out on the basis of the model. A test facility was developed to carry out full-scale tests. According to the experimental studies, the model was refined, which made it possible to obtain a discrepancy in the results of no more than 2.5 Hz.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):36-46
pages 36-46 views
Models for determining the orientation of the solar battery of an observation spacecraft relative to the Sun during object survey and retargeting
Kurenkov V.I., Pupkov E.A.

Simplified models and algorithms have been developed to estimate the current value of the angle between the normal to the plane of the solar panel and the sun vector at the time of object survey and during the reorientation of the Earth remote sensing spacecraft, taking into account the relative movement of observation objects in the field of view of the spacecraft. The models differ from the existing ones in that they do not require knowledge of the spacecraft control programs at pitch, roll and yaw angles at each moment of time of the process of its targeted functioning and re-targeting, Based on the obtained models, a software module that does not require large computing resources used in the simulation software package simulating targeted functioning of the space surveillance system has been developed, taking into account the long-term orbital motion of satellites, changes in the parameters of the orbit, the sun vector and other factors. The adequacy of the developed models was verified by visualizing the orbital motion of the spacecraft and its turns during re-targeting, as well as by comparing the simulation results with the results of analytical calculation for particular cases of the initial data. Examples of the implementation of software windows are given.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):47-58
pages 47-58 views
Determining aerodynamic characteristics of small unmanned aerial vehicles involving flight experiment
Lukyanov O.E., Zolotov D.V., Espinosa Barsenas O., Komarov V.A.

The methodology, software and hardware and the results of determining the aerodynamic characteristics of a small-sized UAV on the basis of a flight experiment are considered in the article. The peculiarity of the proposed technique is the use of small-sized UAVs to study the aerodynamic characteristics of various aerodynamic configurations and new engineering solutions. The main feature of the software and hardware implementation of the methodology consists in the use of small-sized electronic elements and electromechanical components available on the market in order to develop a sufficiently universal system of airborne measurements. The description and technical characteristics of the developed system are given. The system was tested on a specially designed and manufactured UAV with a traditional aerodynamic configuration that was designed using well-known and sufficiently reliable aerodynamic characteristics for such aircraft. The results of processing the data of the flight experiment and the aerodynamic characteristics calculated on its basis are presented. They show fairly good agreement with the parameters laid down in the design of the experimental UAV.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):59-74
pages 59-74 views
Features of design calculation of compressor spool flow path of a twin-shaft gas turbine engine core on the basis of 1D and 2D models of their working process
Matveev V.N., Goriachkin E.S., Popov G.M., Baturin O.V., Kudryashov I.A.

The features of the stages of parameter design calculation for the formation of the initial design of the flow path of the compressor spool of a twin-shaft engine core of a gas turbine engine are presented and substantiated. The article contains recommendations for choosing values of the pump head coefficient, efficiency and other important parameters for the  stages of medium-pressure and high-pressure spools at the stage of thermodynamic calculation. At the stage of design gas-dynamic calculation of the compressor at the middle diameter, typical distributions of axial velocity component and degree of reaction along the flow path of compressor spools should be taken into consideration. At the same time, it is necessary to provide requirements for reducing the flow velocity and static pressure coefficients in the rotor wheels and stator blades, head coefficients and Stepanov coefficients. The design gas-dynamic calculation of the compressor along the radius of the flow path is characterized by a variety of flow swirl laws at the inlet to the rotor wheels, distributions of the pressure increase and efficiency over the height of the blades. In conclusion, an example of a three-dimensional model of a compressor flow path taking into consideration the features of design calculation of the parameters of compressor spools of a twin-shaft engine core of a gas turbine engine on the basis of the appropriate flow path diagram in the meridional plane is presented.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):75-88
pages 75-88 views
Assessment of the possibility of shortening the landing distance of maneuverable aircraft
Strelets M.Y., Tarasov A.Z., Grishin I.A.

The problem of implementing the landing of a maneuverable aircraft by a pilot on an undamaged section of a runway of minimum length is considered. A method of landing the aircraft is proposed, including movement along the landing glide path with minimum speeds and angles of attack of 12-14 deg., the release of the landing parachute before touching the runway with the main wheels so that by the time the wheels touch the ground, the parachute fully opens, lowering the nose wheel and subsequent braking with maximum deceleration. A simplified mathematical model is considered that makes it possible to estimate the length of the run and the results of calculations for various parameters of the landing mass and the height of the release of the braking parachute. The results of such landings in flight tests are presented and compared with the results of calculated estimates. The calculated and experimental results obtained allow us to speak about the fundamental feasibility of the task of landing on a runway section limited in length.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):89-98
pages 89-98 views
Bench tests of an electric engine-propeller group, as the first stage in the creation of a hybrid power plant
Sychev A.V., Ravikovich Y.A., Borisov D.A.

The article discusses a stand for testing an electric propulsion system and its components. The test bench was developed for the first stage of practical research on the creation of a hybrid parallel- circuit power plant based on a piston and electric motors. The engine-propeller group was created for light aircraft with an engine power of 10…20 kW. The article presents conclusions about the conducted bench tests and the operation of the stand. Further developments of an electric motor-generator set for a hybrid power plant made on the basis of bench experiments of the electric engine-propeller combination are shown.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):99-107
pages 99-107 views


Approximation of forces of fluid film bearing lubricating layer using machine learning methods
Kazakov Y.N., Stebakov I.N., Shutin D.V., Savin L.A.

The article analyzes the application of various machine learning methods for solving the problem of approximating the forces of fluid film bearing lubricating layer in static formulation. The initial data on the values of lubricating layer forces for different shaft positions were obtained using a model of a rotor-bearing system based on the numerical solution of the Reynolds equation, with account for the cavitation effect. Methods for reducing the amount of calculation required to obtain the necessary data set are determined on the basis of analyzing solution approximation accuracy with artificial neural networks. After that, approximation models were constructed using a number of other machine learning methods, and the accuracy of predictions as well as the duration of the training process were analyzed. Finally, conclusions were drawn about the most effective approaches to building such models.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):108-121
pages 108-121 views
Abrasive flow machining of specimens of cast billets from austenomartensitic steel with high-viscosity media
Levko V.A., Teryaev N.S., Litovka O.V., Ivanov P.A.

The paper presents the results of research on abrasive flow machining of removable specimens of cast billets made of austenomartensitic steel placed in a simulator of a closed curvilinear channel. The change in the roughness and micro-hardness of the surface of the samples was evaluated. There are two stages of machining. At the first stage of machining, most of the casting skin is removed. At the second stage, the casting skin is removed completely and the base metal layer is removed. It was established that the main mechanism for removing material from the surface of a cast billet is microcutting at the level of elementary real areas of contact of individual grain micro-protrusions. According to the results of the experiments, it is recommended to use abrasive flow machining with highly viscous medium to improve the roughness and increase the micro-hardness of the inner surfaces of the closed channels of cast billets.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):122-132
pages 122-132 views
Experimental method for evaluating the balance of high-speed small-sized internal combustion engines
Rekadze P.D., Sychugov S.Y., Melentiev V.S., Rodionov L.V.

The article presents an adaptation of the Gaevsky-Zhidkov method for estimating the balance of high-speed small-sized internal combustion engines using the idle characteristic, as well as propeller and external speed characteristics. The main task was to develop a test bench that provides high accuracy, repeatability of measurements and the ability to test internal combustion engines with working volume of up to 3.5 cm3 at shaft speeds of up to 37,000 rpm. The test bench makes it possible to determine the characteristics of the “engine-propeller”, the no-load characteristic, and also to carry out quick reconfiguration of the test facility when changing the internal combustion engine structure. As a result of the experimental study, the propeller characteristics of seven propellers, the no-load characteristics for the base electric motor and an electric motor with imbalance were determined. Using these results, the external speed characteristics of an internal combustion micro-engine with working volume of 2.5 cm3 were compared for two levels of balancing.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):133-142
pages 133-142 views
Comparison of quasi-three-dimensional and full three-dimensional formulations of thrust bearing operation
Sokolov N.V., Khadiev M.B., Fedotov P.E., Fedotov E.M.

The results of calculating the characteristics of a thrust bearing with fixed pads of a centrifugal or screw compressor, determined on the basis of a numerical implementation of a periodic thermoelastohydrodynamic mathematical model in quasi-three-dimensional and full three-dimensional formulations, are compared. In the first case, the energy equation is solved on the middle radius of the bearing, and the result of the calculation is extended to the entire fluid flow of the lubricant film and boundary layer (Sm2Px2T program). In the second case, the full three-dimensional equation of the energy of the lubricant film and boundary layer, the thrust collar and the pad is solved, taking into account the heat exchange between the working areas of the bearing and with the environment (Sm2Px3Txτ program). Appropriate conclusions are made.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):143-159
pages 143-159 views
Exploratory analysis of hybrid polymer metal-composite structures
Khaliulin V.I., Petrov P.A., Kostin V.A., Levshonkov N.V.

The results of research in the field of development of technology for the manufacture of hybrid composites according to the scheme of directional fiber netting are presented. Reinforcement is carried out by combining carbon fibers and metal wire, impregnation with a polymer binder by infusion. The results of experimental evaluation of the tensile strength of composites reinforced only with wire, as well as hybrid samples with different percentages of carbon and metal fibers are presented. A significant dependence of the strength of the hybrid composite on the volume ratios of reinforcing materials and technological factors has been established. Design and technology recommendations aimed at improving the functional parameters of the hybrid composite are formulated.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2023;22(3):160-175
pages 160-175 views

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