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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DOAJ

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

Vol 20, No 2 (2021)

Full Issue

AIRCRAFT AND SPACE ROCKET ENGINEERING

System of differential equations of aircraft spatial motion dynamics with arbitrary tensor of inertia and center of gravity position
Vereshchikov D.V.
Abstract

Derivation of analytic expressions making up the basis of a mathematical model of aircraft flight dynamics for the differential equations describing the change in the rate of roll, yaw and pitch, as well as flight velocity components in projections on the body-fixed coordinate axes is presented. The origin of the coordinate system does not in general coincide with the center of mass of the plane, and the axes are not the same as its main central axes of inertia. The differential equations for angular and linear velocities are reduced to the form convenient for the use of numerical methods and computer systems and make it possible  to get consistent results of simulating the dynamics of aircraft spatial motion with an arbitrary tensor of inertia and center of gravity position.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):7-18
pages 7-18 views
Calculation of flow characteristics of liquid fuel supplied through pressure jet atomizers of small-sized gas turbine engines
Gurakov N.I., Zubrilin I.A., Hernandez Morales M., Yakushkin D.V., Didenko A.A., Matveev S.G., Komisar Y.V.
Abstract

The paper presents the results of studying the flow characteristics of liquid fuel in pressure jet atomizers of small-sized gas turbine engines with nozzle diameters of 0.4-0.6 mm for various operating and design parameters. The study was carried out using experimental measurements, semi-empirical correlations and CFD (computational fluid dynamics) methods. The Euler approach, the volume- of- fluid (VOF) method, was used to model multiphase flows in CFD simulations. Good agreement was obtained between experimental and predicted data on the fuel coefficient and the primary spray cone angle at the nozzle outlet. Besides, the assessment of the applicability of semi-empirical techniques for the nozzle configurations under consideration is given. In the future, the flow characteristics in question (the nozzle flow rate, the fuel film thickness, and the primary spray cone angle) can be used to determine the mean diameter of the droplets (SMD) required to fully determine the boundary conditions of fuel injection when modeling combustion processes in combustion chambers of small-sized gas turbine engines.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):19-35
pages 19-35 views
Designing of control and expulsion equipment for the pitot-static system of passenger airplanes
Zotin N.A., Lisman E.P.
Abstract

The article discusses the issue of automating the serial process of bleeding and control of the pitot- static system of passenger airplanes. A functional diagram and basic design of some parts of the combined equipment are proposed. This equipment makes it possible to alternate the above-mentioned operations with great effectiveness. At the system control stage, the pressure or vacuum in it is created by a pressure-vacuum pneumatic unit. This pneumatic unit consists of a compressor and a set of electromagnetic valves that allow the compressor to be connected to the pumping or scavenging line. The value of the generated pressure is regulated by the flow rate in the pressure/scavenging channel and in the venting channel. Simulation of changes in ambient temperature is achieved due to blowing heated or cooled air over the temperature sensors of the aircraft. Pressure or vacuum in the controlled system is created in turn, in each of its lines. At the expulsion stage, a compressed-nitrogen cylinder acts as the pressure source. The pressurized gas passes through the pitot and is released into the atmosphere, cleaning out the contaminations. No manual operations are required for installing and removing connection hoses after connecting the proposed combined equipment to the pitot-static system. Remote-controlled electromagnetic valves connect the channels of the controlled system to the pressure-vacuum pneumatic unit and the source of compressed nitrogen. This reduces the duration of successive operations for the system’s maintenance.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):36-44
pages 36-44 views
Optimal design of sandwich floor panels made of high-strength composite materials considering stiffness constraints
Komarov V.A., Pavlova S.A.
Abstract

The article considers the challenge of designing sandwich floor panels made of high-strength composites considering stiffness constraints. A dimensionless criterion is proposed for assessing the stiffness of floor panels. A new constraint equation determines an interrelation between geometrical parameters of composite constructions and a given criterion. A demo example and the results of designing a typical floor panel using a high-strength composite material are presented. The mass of a square meter of the structure is considered as an objective function, and the thickness of the skin and the height of the honeycomb core of a sandwich construction are considered as design variables. In order to find the optimal ratio of design variables, a graphical interpretation of the design problem is used considering strength and stiffness constraints in the design space. It is noted that the presence of restrictions on a given value of the permissible relative deflection leads to an increase in the required height of the honeycomb filler with an insignificant consumption of additional mass of the sandwich construction.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):45-52
pages 45-52 views
Mathematical model of acoustic characteristics of polyurethane foam used for sound absorption in aerospace engineering
Kuznetsov A.V., Igolkin A.A., Safin A.I., Pantyushin A.O.
Abstract

When solving the problem of reducing the acoustic load on the spacecraft during the launch and flight of the launch vehicle, finite element modeling of acoustic processes under the nose fairing is carried out. To successfully solve this problem, a mathematical model of the acoustic characteristics of the material used for sound insulation is required. The existing mathematical models of the acoustic characteristics of materials are not suitable for the material under consideration that can be used in rocket and space technology to increase the sound insulation of the payload fairing + transfer compartment assembly. To obtain the sound absorption coefficient of the material, an impedance tube measurement method with two microphones is used. Using the method of differential evolution, the coefficients of a mathematical model of acoustic characteristics of the Delany-Bazley type for the specified material are selected. The sound absorption coefficient obtained experimentally and that calculated using the obtained model are compared; the average and maximum values of the error are shown. The resulting model will make it possible to carry out finite element modeling of acoustic and vibroacoustic processes under the nose fairing, taking into account the location of the sound-absorbing material.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):53-62
pages 53-62 views
Deployment and stabilization of the motion of a space tethered system in a lunar orbit
Ledkova T.A., Zabolotnov Y.M.
Abstract

The motion of a space tether system, consisting of a constellation of two microsatellites and a space station, is investigated. The station moves in a circular undisturbed circular lunar orbit. The process of deployment of tethers to bring the system into a working near-vertical condition is considered. A program for controlling the tether tension force that ensures the deployment of tethers to the required length and stabilizes the system in the vertical position is proposed. A study of the stability of the equilibrium position of a mechanical system is carried out. It is shown that the motion carried out during the deployment of a tethered system according to the program proposed in the work is asymptotically stable.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):63-73
pages 63-73 views
Three-dimensional inhomogeneous thermal fields of the “Photon-Amur 2.0” payload electronic board developed for nanosatellites
Fomin D.V., Barulinа M.A., Golikov A.V., Strukov D.O., German A.S., Ogorodnikov A.A.
Abstract

The thermal fields of the “Photon-Amur 2.0” payload electronic board developed for nanosatellites were studied. The “Photon-Amur 2.0” payload consists of an electronic control board with a casing mounted in a nanosatellite and a remote panel with experimental photovoltaic converters. A modified heat balance method was used for numerical simulation of the thermal fields of the control board and the casing. The constructed model and the obtained results of the numerical simulation were verified by comparison with the thermal diagrams obtained for the “Photon-Amur 2.0” electronic board under normal operating conditions. For modeling the outer space operating conditions, it was assumed that there is a vacuum outside and inside the “Photon-Amur 2.0” casing, and the thermal effect is transmitted from the nanosatellite racks to the payload electronic board through the fastenings. The thermal effect is of a periodic nature with amplitude of –45 to +80C and a period of 96 min, which approximately corresponds to the motion of a nanosatellite in a 575 km-high orbit. It was demonstrated that with such composition of the payload module, its casing can work as a passive thermoregulator of thermal fields on the electronic board of “Photon-Amur 2.0”. The simulation showed that the casing helps to keep the temperature on the control board in the interval of –15°C to +85°C, which is acceptable for the electronic components used on the payload control board.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):74-82
pages 74-82 views

MECHANICAL ENGINEERING

Model for evaluating the end runouts of a rotor with parallel connections of parts
Grachev I.A., Kudashov E.V., Bolotov M.A., Pronichev N.D.
Abstract

The existing methods for calculating the assembly dimensional chains of aircraft engine rotors are analyzed. The factors that have a significant impact on the reliability of the calculation of the controlled assembly parameters of the product are identified. One of these factors is the existence of parallel connections of parts in the rotor. In the drum & disk rotors, parallel rotor connections are formed by mating their parts along several end surfaces in the axial direction. A mathematical model is proposed that allows taking into account the parallel connections of the rotor parts. The form of relationship between rotor end run-outs and amplitudes of deviations of the shape of the mating surfaces of the parts and their angular positions in the unit is determined. The determined dependence includes many coefficients that allow taking into account the amplitudes of deviations of the shape of the mating surfaces, parallel connections of parts in the rotor, and their angular position. Determination of dependence coefficients’ values is solved as a problem of regression analysis. The initial data for obtaining the dependence are formed using the developed parameterized finite element model (FEM) of a part of the rotor of an aircraft engine high-pressure compressor (HPC). The results of research of end run-outs of control surfaces of disks of the considered HPC rotor assembly part are presented. The values of the dependence coefficients for assessing the end run-outs of the rotor are determined.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):83-96
pages 83-96 views
An experimental study of the influence of valve drive type on the dynamic loading and service life of valve seals of units
Kondrashov Y.I., Ermilova E.N., Vidyaskina A.N.
Abstract

The article discusses an experimental study of the influence of the valve drive type on the dynamic loading and service life of valve seals of units. The results of research of the modes of closing of piston valves and bellows valves at different response speeds are presented. The differences in the amplitude characteristics of repeated impact, arising from the rapid return motion of the valve’s trim, in the piston and bellows versions of the valve are established. The influence of the operating mode on the service life in both versions of the valve design was assessed, and pressurized leakage tests were also carried out.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):97-104
pages 97-104 views

JUBILEES OF SCIENTISTS

Professor A.P. Merkulov’ role in the process of research and development of the vortex effect
Biryuk V.V., Lukachev S.V., Volov V.T., Pirallishvili S.A.
Abstract

The article is prepared for the centenary of the birth of Alexander Petrovich Merkulov. The stages of creating the theoretical basis of the vortex effect of energy separation of gases (the hypothesis of vortex interaction), and the creation and implementation of vortex devices based on the use of the vortex effect for aviation and medicine are considered. The role of Professor A.P. Merkulov in the study of characteristic features of the energy separation process in vortex tubes and practical application of the vortex effect in the USSR is shown. The works of ONIL-9 (KuAI-SGAU) headed by Alexander Petrovich Merkulov ensured the leading position of the Soviet school of thought in the field of vortex effect. These works contributed to the formation of modern understanding of the vortex effect and the successful beginning of industrial application of vortex apparatuses.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2021;20(2):105-121
pages 105-121 views

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