Rubric: "05.07.00 Aviation and Rocket-Space Engineering"



521.2:521.3:521.61 Evolution of the orbit of a passive fragment with a large area of surface in high Earth orbit

Bazey A. A. (Scientific Research Institute “Astronomical Observatory” of Odessa Mechnikov National University), Bazey N. V. (Scientific Research Institute “Astronomical Observatory” of Odessa Mechnikov National University), Borovin G. K. (Keldysh Institute of Applied Mathematics of the Russian Academy of Scienсes), Zolotov V. E. (Keldysh Institute of Applied Mathematics of the Russian Academy of Scienсes), Kashuba V. I. (Scientific Research Institute “Astronomical Observatory” of Odessa Mechnikov National University), Kashuba S. G. (Scientific Research Institute “Astronomical Observatory” of Odessa Mechnikov National University), Kupriyanov V. V. (The Central Astronomical Observatory of the Russian Academy of Sciences at Pulkovo), Molotov I. E. (Keldysh Institute of Applied Mathematics of the Russian Academy of Scienсes)


doi: 10.18698/2309-3684-2015-1-8393


We have analysed and presented observations of artificial celestial body 43096. We obtained the observations in 2006–2012 within the project “Scientific Network of Optic Instruments for Astrometric and Photometric Observations” (ISON). We have determined the Kepler orbit elements and state vector as of 1 hour 55 minutes 50,76 seconds, November 24, 2006 UTC (1:55:50,76 November 24,2006 UTC). We have performed numerical integration of the motion equations, taking into account the perturbations from the polar compression of the Earth, the Moon, the Sun and the solar radiation pressure. We propose a method for deorbiting artificial celestial bodies in high altitude orbits. The method is based on a numerical model of motion in circumterrestrial space, which takes into account only the largest perturbations. For the first time ever we have obtained such a great amount of data on objects with a large area of surface to mass ratio over long time spans. The data allowed us to study the objects and reveal their peculiar properties.


Bazey A., Bazey N., Borovin G., Zolotov V., Kashuba V., Kashuba S., Kupriyanov V., Molotov I. Evolution of the orbit of a passive fragment with a large area of surface in high Earth orbit. Маthematical Modeling and Coтputational Methods, 2015, №1 (5), pp. 83-93



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



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



51-71:74 Long-period oscillations of aircraft at hypersonic speeds

Sidnyaev N. I. (Bauman Moscow State Technical University), Glushkov P. A. (Bauman Moscow State Technical University)


doi: 10.18698/2309-3684-2014-1-99114


The article presents the theoretical analysis of the long-period (phugoid) aircraft oscillations, which has a lifting force and performs a flight at hypersonic speeds in any atmosphere. Oscillations are caused by mutual transition of kinetic energy into potential energy during the flight along the path having an oscillatory character and being determined primarily by controlled longitudinal zero momentum in steady flight. The study shows that with the speed approximating to the first cosmic speed, the decrease in gravity at height dominates the decrease in density of the atmosphere, so that with increasing speed the period of phugoid oscillations tends asymptotically to the corresponding period of the satellite. During the research there were obtained analytical expressions for the short-period oscillations or vibrations at the angle of attack. The study demonstrates that these expressions, as well as the expressions for the long-period oscillations are in good agreement with numerical solutions.


Sidnyaev N., Glushkov P. Long-period oscillations of aircraft at hypersonic speeds. Маthematical Modeling and Coтputational Methods, 2014, №1 (1), pp. 99-114



533.6.011.31.5:532.582.33 Calculation of the pressure when streamlining blunt bodies with small supersonic speeds

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


doi: 10.18698/2309-3684-2015-3-5867


The article considers the problem of determining the pressure on the body surface streamlined by a gas flow with a small supersonic speed (M < 1,5).The economic algorithm for calculating the pressure on the part of the surface of blunt bodies of revolution is developed. Examples of flow calculations over spheres and ellipsoids with different semi-axes ratios are presented. Comparison with accurate numerical calculations shows the effectiveness of the proposed approach.


Kotenev V., Sysenko V. Calculation of the pressure when streamlining blunt bodies with small supersonic speeds. Маthematical Modeling and Coтputational Methods, 2015, №3 (7), pp. 58-67



533.6.011.31.5:532.582.33 Analytical formula with improved accuracy for calculating pressure distribution on the surface of convex, blunt rotation bodies of arbitrary shape

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


doi: 10.18698/2309-3684-2014-1-6881


The authors developed the analytical formula for fast and accurate calculation of pressure on the surface of rotation bodies with arbitrary shape, which were flown by supersonic gas. The paper provides examples of applying the method for three-dimensional flows of gas.


Kotenev V., Sysenko V. Analytical formula with improved accuracy for calculating pressure distribution on the surface of convex, blunt rotation bodies of arbitrary shape. Маthematical Modeling and Coтputational Methods, 2014, №1 (1), pp. 68-81



539.3 Computational modeling of conjugated gasdynamic and thermomechanical processes in composite structures of high speed aircraft

Dimitrienko Y. I. (Bauman Moscow State Technical University), Koryakov M. N. (Bauman Moscow State Technical University), Zakharov A. A. (Bauman Moscow State Technical University), Stroganov A. S. (Bauman Moscow State Technical University)


doi: 10.18698/2309-3684-2014-3-324


In the article we propose an algorithm for the numerical simulation of conjugate gasdynamic and thermomechanical processes in composite structures of high-speed aircraft. The algorithm allows calculating all parameters of the three-dimensional gasdynamic flow near the surface of the aircraft, heat exchange on the surface, heat and mass transfer processes in the internal structure of thermodestructive polymer composite, as well as processes of composite construction thermodeformation, including the effects of changes in the elastic characteristics of the composite, variable thermal deformation, shrinkage caused by thermal degradation, building up interstitial gas pressure in the composite. An example of numerical simulation of conjugated processes in a model composite construction of high-speed aircraft illustrates the possibilities of the proposed algorithm.


Dimitrienko Y., Koryakov M., Zakharov A., Stroganov A. Computational modeling of conjugated gasdynamic and thermomechanical processes in composite structures of high speed aircraft. Маthematical Modeling and Coтputational Methods, 2014, №3 (3), pp. 3-24



629.762 Aircraft motion parameters recovery from the data of their discrete registration. Part 2. Methods using regularization

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


doi: 10.18698/2309-3684-2016-2-3954


The article examines methods of aircraft motion parameters recovery from the data of their low resolution recordings in the gas-dynamic ejection experimental test.


Plyusnin A. Aircraft motion parameters recovery from the data of their discrete registration. Part 2. Methods using regularization. Маthematical Modeling and Coтputational Methods, 2016, №2 (10), pp. 39-54



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



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