With cash-developed software system, were carried out research on the impact velocity crosswinds on the position of vortex wake at takeoff and landing of aircraft of various classes. Identify the threat, in terms of "hovering" of wing vortex over the center of the runway, crosswind speed. During takeoff and landing aircraft, these vortices can be a danger to other aircraft.

With application of the developed calculation-software package there were conducted the researches, demonstrating the possibility of in-flight refueling of civil aircraft. As a flying tanker there were chosen tanker aircraft ILyushin-78 which is currently operated and a perspective tanker on the basis of ILyushin-96-400T aircraft. Perspective aircraft MC-21-400 was chosen as an aircraft to be refueled.

New modification of the vortex element method which uses closed vortex loop to calculate the incompressible 3D-flow around bodies by flow of an incompressible medium and determining the unsteady hydrodynamic loads is considered. An original algorithm for closed loops generation on the surface of the body simulation and their evolution in the stream is proposed. The results of algorithm tests is discussed. The model problems of the flow around sphere and cylinder is investigated. It is shown that the results obtained in the pressure distribution on the body surface calculation are in good agreement with the experimental data.

The article provides an overview of cases of stiffness, leading to inadequate results of mathematical models of mechanics. An attempt is made to generalize look at this phenomenon for body dynamics, and for the continuum mechanics. Proposed wording of display of stiffness properties of the mechanical systems, the primary cause of unstable solutions and makes recommendations for the development of sustainable calculation metods.

The possibility of the improved quadrature formulae of the discrete vortexes method used in the aeroelasticity problems is considered. Some of the calculation results confirm the efficiency of these formulae are carried out.

Numerical simulation of flow around a nose fairing half of a launch vehicle was carried out, aerodynamic characteristics of the model were calculated at subsonic and transonic flow velocities, the flow patterns around a thin shell were analyzed.

The research of unsteady vortex flow influence on the aerodynamic control and stabilizing surfaces is carried out. There are defined pulsation aerodynamic characteristics of flight controls with using the open software OpenFoam. The results of the numerical calculations of flow around brake flap and set behind him vertical stabilizer. The pulsation load on the pitching-stabilizer, due to the presence of a brake flap installed at different angles of deflection was calculated. To reduce the pulsation load offered the option of perforated brake flap.

The article examines influence of quality of external surface to change lift aircraft.

The main purpose of this work was the simulation of turbulent thermal flows, which is aimed at improving the visualization and the modeling of the flow fields of wind flows, which are necessary for aviation. The physical-mathematical model of gas flow in thermal is proposed on the basis of thermodynamic model and dynamic model under the assumption that the condensation energy, when the movement of the thermal is upward, becomes the turbulent fluctuations. A thermal is an air mass, which goes up and is capable to intermix with ambient air. In the work the thermodynamic model of thermal is presented, the equations and the system of equations are derived, that describe the main characteristics of wind flow, which are required for the modeling of airflows. The generation of vertical turbulent gust with von Karman spectrum is shown. The basic assumption in the construction of the dynamic model of generation was that the energy, which is stood out in the thermal due to the condensation of steam, is converted into the energy of turbulent pulsations. Some examples of numerical simulation are given in the article. The visualizations of the generation of the vertical velocity of random wind gust are given depending on the size of the considered space and depending on the pitch of cell partition. The analysis and comparison of the obtained results of the calculation are presented. The conducted studies are aimed at the simulation of the atmospheric background and atmospheric processes and, in the final result, at the increasing of flight safety.

In this paper the possibility of using hydraulic analog simulation in the study of problems of unsteady gas dynamics is considered. The analysis of differential equations of unsteady motion of bodies in supersonic flow using the theory of similarity and dimensional analysis. Obtained similarity criteria that must be identical for both the real gas flow and the modeling of fluid flow. Using a hydraulic analog modeling for research in non-stationary gas dynamics provides valuable information necessary for understanding the physics of the processes and the construction of more sophisticated mathematical models.

The results of computational simulation of helicopter rotor's single blade flow, for which experimental (model test) data are published, are represented in this article. The calculations were made in the universal software package of CFD modeling FloEFD, which was based on the solution of averaged equations' system of Navier-Stocks, as well as in the program software RC-VTOL using the vortex method. The obtained results are compared with experimental data and modeling results in the program software ANSYS Fluent (license of TsAGI Nr. 501024). The work shows satisfactory, and in some cases good calculation data reconciliation getting with different techniques including experimental.

This article provides information about the properties of BENT inductive vortices capable of under the influence of self-induction to move at a speed independent of circulating Г, the size of the nucleus and the local curvature of the individual sections of vortex tube. For numerical calculations the method of accounting for the self-induction at the nodal point of the vortex tube segments. Formulas and recommendations for the construction of models the free-vortex wake in the rotor blade theorie

The article presents the results of numerical studies of aerodynamic characteristics of isolated three-bladed tail rotor, and X-shaped tail rotor at "vortex ring". Calculations of aerodynamic characteristics of rotors are based on nonlinear blade vortex model developed at the Department of "The helicopter design" MAI. Considered hover and blasting at positive angles of attack α_H, including the area of "vortex ring". Built "vortex ring" area in the coordinates of the horizontal V_x and vertical velocity V_y of airflow at different angles of attack of the rotor by condition drop rotor thrust against hover thrust at fixed angles of rotor collective pitch.

The results of the helicopter dynamics research after the discharge of cargo transported on the external sling. These results allows to specify the limits of safe modes of transportation and to develop recommendations for actions in particular situations associated with discharge of the cargo are presented.

In this paper we propose a method of constructing a mathematical model of the TsAGI’s compressor transonic wind tunnel T-106 as a Mach number control object. The mathematical model is sought in the form of a family of linear transfer functions with constant coefficients and delay. Experimental investigation of dynamic properties of the wind tunnel T-106 as an object of Mach number control in the subsonic range is provided. The coefficients of the mathematical model of the wind tunnel T-106 is identified on basis the experimental data.

Paper contains description of the construction of aircraft model for aerodynamic experiment in subsonic wind-tunnel, during it rotation. The technique of the experiment, and features associated with rotation were mentioned. Provided the results of measuring Magnus force and it comparing with analytical methodology.

The paper carried out a comparison of vibration sensors used to measure the vibration condition units with gas turbine engines, with motion sensors, microelectromechanical systems used in modern mobile devices (for example, devices on the platform "Android"). It provides opinions on the possibility of assessment of vibration, using sensors of mobile devices.

To determine the operating fields of the tolerances of hydraulic systems parameters for various conditions of work and phases of flight given mathematical relationships and the results obtained in Mathcad in analytical form for the board computer system.

The results of numerical research of lifting and transport system of aircraft vertical takeoff and landing, based on the use of the Magnus effect are presented. The formulas for determining its lift and thrust are obtained. The method of engineering calculation of the basic elements of the system based on the data of experimental aerodynamic tests is developed.

It remains urgent problem of damping of elastic vibrations occurring aircraft structure means the automatic control systems on board. In solving this problem the aircraft elastic model is the basis for the synthesis of control laws and analysis of closed-loop system "control object - the regulator." In general, the problem of mathematical modeling of flight dynamics of the elastic aircraft breaks for at least another two objectives, one of which - direct simulation of the behavior of elastic aircraft defined interacting forces, and the other - the account of the changes operating aerogidrodynamic forces and moments caused by the deformation elastic aircraft and work control systems. This paper discusses the theoretical basis of the approach to the solution of this problem, based on the replacement of the actual design of aircraft by equivalent circuit and its implementation for the missiles, the most simple in terms of schematic, class of aircraft. At the same time accounting for changes in aerodynamic forces and moments caused by the elastic deformation of the aircraft, it was performed by help of stationary hypothesis

The article is addressed to the analysis of the videos obtained during flight experiment at the launch of meteo-rocket MMP-06 in order to determine main characteristics of the oscillatory process the edges of the canopy at subsonic speeds at altitudes from 42,2 km to 34.2 km. Data analysis demonstrated that the oscillations of the edge of the canopy has a random character. The structure frequency of 2.4 Hz was identified from the analysis to be determined by the nylon sling stiffness.

The results of numerical research of aerodynamic characteristics of airship with or without gondola in steady movement of the airship through the atmospheric jet streams. The influence of gondola and location of the airship relative to the axis of the jet stream on the value of the aerodynamic coefficients of airship is defined.

The article deals with known cases of operation of seaplanes and amphibians in the snow-covered surfaces. On the basis of the existing data on the resistance and acceleration acting on the hull of planing snowplane analysis of possible acting on the bottom of the amphibious aircraft weighing 37 tons moving in the snow-covered surface was carried out. Estimates have shown the possibility of the takeoff of such plane while moving in the snow-covered surface. Vertical acceleration and landing hit will not exceed the maximum permissible value if the thickness of the snow cover is not less than 1 meter.

This article discusses the air cushion chassis with multi-section air cushion, designed in NIMK CAHI. This chassis is formed by separate flexible changeable running elements of an advanced design, which are mounted on the balloon part of an air cushion. Aerohydrodynamic and buffer characteristics of this chassis are achieved through experimental work on the plants and in the experimental pond in NIMK TSAGI.

This article describes a first approximation of a weighted estimate of air cushion chassis. The algorithm for calculating the weight of air cushion chassis allows not only to estimate the mass of the chassis to a first approximation, but also to conduct a preliminary analysis of the influence of various parameters of the aircraft and the chassis on the weight of the aircraft at the stage of before designing. The algorithm can be expanded to include additional design decisions, such as the transformation of the fuselage, increasing the air cushion chassis canopy due to extensions, center of gravity, etc.