Rubric: "05.07.00 Aviation and Rocket-Space Engineering"



629.762 Pressurization parameters simulation of container empty space during aircraft gas dynamic ejection considering real gas properties

Plyusnin A. V. (Bauman Moscow State Technical University/JSC MIC NPO Mashinostroyenia)


doi: 10.18698/2309-3684-2016-3-5378


The article considers the pressurization process of a container empty space with the help of a high-pressure cylinder, which antecedes the gas dynamic ejection of an aircraft. Comparative calculations of this process were done in the quasi-stationary approximation using equations of state for both ideal and real gases. The article shows the necessity of accounting deviations in thermodynamic properties of the operating medium from the ideal-gas behavior in order to estimate correctly both gas reserves in the cylinder and temperature variations in the pressurized volumes.


Plyusnin A. Pressurization parameters simulation of container empty space during aircraft gas dynamic ejection considering real gas properties. Маthematical Modeling and Coтputational Methods, 2016, №3 (11), pp. 53-78



629.78 Mathematical modelling of deployment of large-area solar array

Bushuev A. Y. (Bauman Moscow State Technical University), Farafanov B. A. (Bauman Moscow State Technical University)


doi: 10.18698/2309-3684-2014-2-101114


We have built a mathematical model for deployment of multibody solar array with a cable system of deployment. On the basis of analysis of the kinematic scheme of deployment system we have chosen the dimensions of the radii of the rollers and gear ratio of the two types of gear mechanisms which provide the preset sequence of fixation of sections. We used Lagrange equation of the second kind for studying deployment of the solar battery array. A distinctive feature of this approach is application of iterative method for taking into account deformation of the cables of synchronizing system. The mathematical model can be used to choose optimal design factors and deployment system performance requirements. It is also valuable for dealing with worst-case situations and verifying the reliability of deployment procedure.


Bushuev A., Farafanov B. Mathematical modelling of deployment of large-area solar array. Маthematical Modeling and Coтputational Methods, 2014, №2 (2), pp. 101-114



629.762:532.5.031 Boundary-element-method modelling of inside and outside non-stationary interaction of aircraft body and liquid

Plyusnin A. V. (Bauman Moscow State Technical University/JSC MIC NPO Mashinostroyenia)


doi: 10.18698/2309-3684-2014-2-77100


The article considers inner and outer problems of non-stationary interaction between aircraft body and incompressible ideal fluid and statement of the problems in the form of boundary integral equations. By inner problems we mean vibration of fuel in tanks and by outer problems we mean determination of additional masses and moments of inertia. We provide formula of efficient solutions for these problems by the boundary element method as applied to bodies of revolution and examples of calculations.


Plyusnin A. Boundary-element-method modelling of inside and outside non-stationary interaction of aircraft body and liquid. Маthematical Modeling and Coтputational Methods, 2014, №2 (2), pp. 77-100



5 Problem solution of aerodynamic design using multiprocessor computers

Bratchev A. V. (JSC MIC NPO Mashinostroyenia), Dubrovina A. Y. (JSC MIC NPO Mashinostroyenia), Kotenev V. P. (Bauman Moscow State Technical University/JSC MIC NPO Mashinostroyenia), Maksimov F. A. (Institute for Computer Aided Design of the Russian Academy of Sciences), Shevelev Y. D. (Institute for Computer Aided Design of the Russian Academy of Sciences)


doi: 10.18698/2309-3684-2015-1-1730


The article discusses a method for constructing an aircraft geometric shape for computing the parameters of aerogasdynamic flow as well as a method of meshing near the model to simulate the flow within the Navier–Stokes equations in the thin layer approximation. The results of the flow simulation are given. The calculations were performed on a multiprocessor computer system.


Bratchev A., Dubrovina A., Kotenev V., Maksimov F., Shevelev Y. Problem solution of aerodynamic design using multiprocessor computers. Маthematical Modeling and Coтputational Methods, 2015, №1 (5), pp. 17-30



629.762 Mathematical simulation of the process of water entering the annular space of a canister during submarine gas-driven aircraft ejection

Plyusnin A. V. (Bauman Moscow State Technical University/JSC MIC NPO Mashinostroyenia)


doi: 10.18698/2309-3684-2017-2-3964


The study deals with a one-dimensional analytical model for computing the loads on the body of an aircraft caused by water entering the annular space of a launch canister. We used potential theory to solve the "external" hydrodynamic problem. Solving Lamé equations for the static case accounts for the strain in the walls of the aircraft and the launch canister.


Plyusnin A.V. Mathematical simulation of the process of water entering the annular space of a canister during submarine gas-driven aircraft ejection. Маthematical Modeling and Coтputational Methods, 2017, №2 (14), pp. 39-64



533.6:51-71 Investigation of the energy and mass transfer influence on the wake flow of supersonic conical models

Sidnyaev N. I. (Bauman Moscow State Technical University), Gordeeva N. M. (Bauman Moscow State Technical University)


doi: 10.18698/2309-3684-2015-1-3149


We studied the dynamics of motion and energy transfer in supersonic flow in the base region. It is shown in the article that the current in the base region largely depends on the boundary layer structure in the area between the trailing edge and the sticking point on the centerline, where the boundary layer cut out from the rear edge converges. The study of the effect of gas mass injection into the base region from the body surface and the bottom as well as heat transfer in the bottom region is included. The resulting solution of the problem of the middle wake for axisymmetric body without considering recirculation at a limited distance from the stern has been obtained.


Sidnyaev N., Gordeeva N. Investigation of the energy and mass transfer influence on the wake flow of supersonic conical models. Маthematical Modeling and Coтputational Methods, 2015, №1 (5), pp. 31-49



533.16 Simulation of gas flow through the laminar boundary layer on the hemisphere surface in a supersonic air flow

Gorskiy V. V. (Bauman Moscow State Technical University/JSC MIC NPO Mashinostroyenia), Sysenko V. A. (JSC MIC NPO Mashinostroyenia)


doi: 10.18698/2309-3684-2014-4-8894


The article presents estimated accuracy of the engineering design procedure of the mass flow rate of gas through the laminar boundary layer on a hemisphere of [1]. A similar engineering method of extra accuracy is proposed.


Gorskiy V., Sysenko V. Simulation of gas flow through the laminar boundary layer on the hemisphere surface in a supersonic air flow. Маthematical Modeling and Coтputational Methods, 2014, №4 (4), pp. 88-94



629.762 Calculation of aircraft gas-dynamic ejection systems with due consideration of the secondary combustion effects

Plyusnin A. V. (Bauman Moscow State Technical University/JSC MIC NPO Mashinostroyenia)


doi: 10.18698/2309-3684-2014-3-5573


The article presents a method of accounting for secondary combustion effects when solid propellant power device is used for the gas-dynamic ejection of lifting vehicles. The method is based on thermo chemistry calculations. The suggested method can be easily applied to engineering calculations of aircraft gas-dynamic ejection systems as well as to the analysis of experimental data involving secondary combustion effects.


Plyusnin A. Calculation of aircraft gas-dynamic ejection systems with due consideration of the secondary combustion effects. Маthematical Modeling and Coтputational Methods, 2014, №3 (3), pp. 55-73



629.735.33.016+621.45.015 Simulating atmospheric conditions influence on flight program optimization for a subsonic passenger aircraft

Mozzhorina T. Y. (Bauman Moscow State Technical University), Gubareva E. A. (Bauman Moscow State Technical University)


doi: 10.18698/2309-3684-2014-3-7488


We examined effects of typical for different climatic zones atmospheric conditions on flight program optimization for a subsonic long-haul passenger aircraft. Simulation of flight and power plant performance was based on current traditional approaches used in solving problems of this kind. The acceleration-climb flight segment has been optimized by minimizing fuel consumption at this flight segment. The cruising flight segment has been optimized considering operating limitations accepted for civil aviation. The in-built model of bypass turbojet engine was used for simulating the flight. This model allows calculating power plant performances under any flight conditions. The flight of subsonic aircraft has been examined in one vertical plane. Calculations have been performed for 6 standard air temperature variations with altitude (depending on climatic zone). Atmospheric pressure variation near Earth surface was considered and effects of atmospheric conditions on flight program optimization were estimated.


Mozzhorina T., Gubareva E. Simulating atmospheric conditions influence on flight program optimization for a subsonic passenger aircraft. Маthematical Modeling and Coтputational Methods, 2014, №3 (3), pp. 74-88



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