The state of the runway (RWY) under operating conditions, due to the possibility of formation of a layer of water, ice, slush, snow, decreases the friction coefficient of the aircraft landing gear to RWY, and may cause the aviation events. In addition, the condition of taxiways and airport runway affects the taxiing time of aircraft, which during high-traffic hours can lead to additional flight delays. To study the effect of friction coefficient on the runway occupancy time the methodology of collecting statistical data about the time of different types of aircraft spent on runway at various values of the friction coefficient is offered. The method is based on a full-scale experiment. To conduct the experiment as the object of analysis the process of moving the aircraft from the holding position up to reaching the height of 200 meters at Vnukovo airport was chosen. Since the observer cannot control the parameters affecting the object of study during the flight, the friction coefficient is recorded as an input parameter during the experiment and as the response – the time of moving aircraft from holding position up to reaching the height 200 meters after take-off on standard departure procedure. As a result of the experiment, according to the obtained data, a graph of Ttot versus friction coefficient was designed. The greatest influence of the friction coefficient is observed when taxiing from the holding position on runway to line-up position.

The authors of this article propose a research technique of unmanned aerial vehicle (UAV) dynamic behavior in ground conditions with account of flight experiment data. Dynamic researches of UAV and separate components of its onboard equipment are one of the most important tasks of the ground testing stage of UAV. The flight experiment gives the most reliable information about the vibration condition of the UAV and its onboard equipment. However to identify the real vibration condition of the UAV requires the installation of a sufficiently large number of accelerometers, which technically can be unrealizable during flight studies. It is proposed to solve this problem by conducting ground dynamic tests. Having determined the nature and level of vibration during the full-scale (flight) experiment in the "reference" places, it is possible further in the laboratory with a high degree of reliability to obtain vibrations (amplitude and phase frequency characteristics, spectrum, etc.) in other places of the UAV construction. To do this, it is necessary to install accelerometers throughout the UAV airframe, including the "reference" places that were used in the flight experiment. By exciting the UAV alternately along the longitudinal and lateral axes with the vibration spectrum obtained in the full-scale experiment, the vibration spectrum is reproduced in those places where accelerometers are installed in the laboratory experiment. In this case, the vibration task is carried out by "reference" accelerometers, as in the full-scale experiment. In the future, the resulting vibration process can be transferred to autonomous studies of the automatic control system and its individual units, actuator, rudder – drive system, etc. to assess their functioning in these vibration conditions. In addition to the main provisions of the technique, the article presents a schematic diagram and an example of the dynamic behavior research of UAV in ground conditions with account of flight experiment data.

The article considers the problem of the flow around the helicopter main rotor taking into account blades flapping in the plane of rotation and in the plane of thrust as well as the elastic blades deformation. The rotor rotation is modeled by the method of converting Navier-Stokes equations from a fixed coordinate system associated with the incoming flow into a rotating system associated with the rotor hub. For axial flow problems, this makes it possible to formulate the problem as stationary at a constant rotational speed of rotor. For a mode of skewed flow around the rotor in the terms of incident flow in this system it is necessary to solve the non-stationary problem. To solve the problem, the method of deformable grids is used, in which the equations are copied taking into account the grid nodes motion determined in accordance with the spatial blades motion, and SST turbulence model is used for closure. The results of the test calculations of the main rotor aerodynamic characteristics with and without blade flapping are presented in this paper. The coefficients of the main rotor thrust cT and the blades hinge moments mh are compared. The calculations were carried out in the CFD software ANSYS CFX (TsAGI License No. 501024). The flow around a four-bladed main rotor of a radius of 2.5 meters is modeled in the regime of skewed flow. The speed of the incoming flow came to 85 m/s under normal atmospheric conditions. The rotor was at an angle of attack of −10˚. To calculate the rotor motion without taking into account the flapping movements, we used the nonstationary system of Navier-Stokes equations with the closure with SST turbulence model. The calculation was being carried out until the change in the maximum value of the rotor thrust during one revolution became less than 1%. For modeling flapping blade movements, the control laws and equations describing the angle of blade flapping as a function from its azimuth angle obtained from the experiment were used. The procedure for reconstructing the grid according to a given law was conducted using standard grid deformation methods presented in the ANSYS CFX software. When solving the nonstationary Navier-Stokes equations, a dual time step was used. The obtained results show that accounting of the effect of flapping movements and cyclic control of the blades has an impact on the character of changing the main rotor thrust coefficient during one revolution and significantly changes the shape of the graph of the hinge moment coefficient of each blade.

Current trends of civil aviation development show a significant increase in the number of aircraft with aircraft piston engines. The Ministry of Transport of the Russian Federation is preparing a draft order on amendments to the Federal aviation rules for the preparation and performance of flights in civil aviation (FAP-128), which stipulate for simplified procedures of paid excursion flights implementation for light and ultralight aircraft and helicopters. It is obvious that this circumstance will significantly affect the expansion of the fleet of these aircraft. Accordingly, the state of piston engines operating on aviation gasoline value questions are becoming increasingly relevant. The current problems of aviation engines diagnostics by metal contents in oils are observed in the article. Their bugs, possible ways of solving this problems and bugs, actual developments in this direction are shown. The application examples of early diagnostic methods using the automated diagnostic complex “Prisma” are shown. The oil samples taken from An-2 aircraft АШ-62ИР piston engine analyses results attract the most interest. They show that with proper training of personnel the valuable information coming from the oil samples can be a source of important conclusions not only in aircraft engines accessories and assemblies state value, but also others systems, and also conclusions about the quality of fuel and lubricants used. Estimating the residual life method of the engine at various stages of its operating time on the metal content in the oils and the procedure for oil selecting, allowing to obtain reliable results, are suggested.

Due to the implementation of new certification requirements for icing conditions provided in Annex О to CS-25, there is a necessity to analyze the impact of the requirements on the possibility of transport aircraft certification for flights under such conditions. The particularities of such certification requirements and their impact on three main directions of aircraft certification have been considered for icing conditions: icing annunciation system, air data system and anti-icing system. It has been shown that new requirements have no effect on certification of air data system sensors but they have an impact on icing annunciation and antiicing system. Timely annunciation of icing is important for safe operation of aircraft. The procedure providing timing annunciation was developed earlier in Annex C to AR/CS/FAR-25. It is highlighted that this procedure is also actual for new icing conditions but taking into account relevant updates in calculations of the growth of ice accretions on ice detectors, air inlets and lifting surfaces. One of the problems is to detect the moment of coming into icing conditions, determined by new requirements. It substantially determines the possibility of immediate escape from icing area if the airplane does not meet the safe operation requirements for such conditions. The techniques of removing ice accretions from lifting surfaces are described. The case of icing the wing surface behind the slats area with barrier ice accumulation was studied. The possibility of an aircraft limitless operation under icing conditions determined by new certification requirements was estimated.

Monitoring technologies are rapidly developing at present and allow to extract and use non-coordinate information about objects. Noncoordinate information is the information about the type and properties of an object under study. Remote sensing is the main method of solving monitoring problems where special positioning belongs to the radar methods, based on space-time processing of signals and, in particular, on methods of radio polarimetry. It is necessary to have information about the surface in order to solve the monitoring task. The slightest changes in the electrical and physical properties of such areas as salinity, humidity, soil composition, etc. will lead to a change in the basic electrodynamics of the surface, notably its complex dielectric permittivity. The article demonstrates the precise solutions to the problems of radio-waves reflection from a layered surface with various laws of changes of the complex permittivity  in depth. Media with exponential and quadratic laws of variation  for arbitrary angles of incidence of the radio wave on the surface are considered. Precise decision is obtained for layered media with the law of change in the complex permittivity the polynomial and linear characteristics. A similar problem for the parabolic layer is considered separately. The detailed analysis of radio waves reflection from the medium with a matching layer is carried out. The nature of the electromagnetic field inside the transition layer is studied in detail. The article is illustrated by the graphs showing the dependences of an electromagnetic wave reflection coefficient on the layered medium with linear and exponential laws of variation of the complex dielectric constant over depth.

The article suggests a modification for numerical fireworks method of the single-objective optimization for solving the problem of multiobjective optimization. The method is metaheuristic. It does not guarantee finding the exact solution, but can give a good approximate result. Multiobjective optimization problem is considered with numerical criteria of equal importance. A possible solution to the problem is a vector of real numbers. Each component of the vector of a possible solution belongs to a certain segment. The optimal solution of the problem is considered a Pareto optimal solution. Because the set of Pareto optimal solutions can be infinite; we consider a method for finding an approximation consisting of a finite number of Pareto optimal solutions. The modification is based on the procedure of non-dominated sorting. It is the main procedure for solutions search. Non-dominated sorting is the ranking of decisions based on the values of the numerical vector obtained using the criteria. Solutions are divided into disjoint subsets. The first subset is the Pareto optimal solutions, the second subset is the Pareto optimal solutions if the first subset is not taken into account, and the last subset is the Pareto optimal solutions if the rest subsets are not taken into account. After such a partition, the decision is made to create new solutions. The method was tested on well-known bi-objective optimization problems: ZDT2, LZ01. Structure of the location of Pareto optimal solutions differs for the problems. LZ01 have complex structure of Pareto optimal solutions. In conclusion, the question of future research and the issue of modifying the method for problems with general constraints are discussed.

A number of aviation assemblies are made as pressure couplings of thin-wall components, e.g., shafts and hubs, durability of which is related to fitting contact load concentrations under cyclic and dynamic loadings. This article discusses a numeric solution to the contact problem. The solution is introducing into the calculations a conventional boundary layer, any shift of which is equivalent to a roughness deformation of fitting surfaces. The mathematical model of a pressure coupling is founded on a division of deformations into general (axisymmetric bending of components) and local deformations (microroughness compression) that are determined independently. To simplify the solution, the dependence of the contact convergence of the surfaces on the pressure is subjected to linearization in the form of a model of a rigid plastic body with linear strengthening. Convergence values in section are only determined by the pressure and do not depend on the stress-and-strain behaviors of areas adjacent to the rough interfacial space. The Green’s functions method is used to find radial shifts of components, while the solution is expressed by the Fredholm integral equation. That is reduced to a finite system of linear algebraic equations when the contact is made discrete. This approach provides solution stability through strengthening of the main diagonal of the resolving system, while the evaluation accuracy of the concentration coefficient depends on the subinterval value. It has been found that any disclosure of a coupling beneath the faces of an enveloping body is practically impossible for that model. The comprehensive approach provides a generalized solution for orthotropic and stepwise shells, as well as for components with specific design features and various strengths of areas adjacent to fitting sites. Deviations of the shape of the contact surfaces from the straightness are taken into account by its respective pressure coupling function. The analysis of the findings suggests that the concentration coefficient value slumps as the contact compliance coefficient of the borderline layer increases. Any shape deviations of the fitting surfaces, including their coning and concavity, increase the contact load concentration, while their convexity causes a reverse effect. We recommend using strengthening treatment methods, e.g., application of regular micropattern in the shape of helical flute at a certain pitch while applying a constant or a variable force on the diamond indenter, or vibration smoothing in order to control the shaft surface finishing to improve the stressand-strain behavior of the seam and to impart an artificial barrel shape of a preset value to the shaft. These technologies compensate contact load concentrations, and, together with the strengthening factor, enhance the fatigue limit of such assemblies.