The profound and qualitative analysis of the work which is carried out by the controller in direct management of the air traffic and preventing aviation accidents is of great importance, since there is a significant number of factors affecting the consequences of any air-traffic event. While analyzing the work of the air traffic controller (ATC), it is necessary to take into account his physical condition, as well as his work experience and age. Careful examination of controller’s internship, retraining and unsupervised work processes is one of the effective accident-preventing methods allowing us to visualize and track the relationship between the identified errors and possible options for minimizing them. In order to make a detailed analysis of ATC performance, each civil aviation enterprise employs the means of objective control and a method of supervision containing a data set of the revealed errors made by the controller while working. The process of monitoring with the help of objective control means makes it possible to identify the drawbacks in the air traffic management while performing each operation, and also to develop a set of measures for preventing aviation accidents in the future. However, it is not always possible to identify problems in time, because they can be hidden from the inspectors intentionally or due to such circumstances as emotional and spiritual experiences of the air traffic controller, provoked both by the activity inside the working environment and beyond it. The notion of a "human factor" is versatile, so it is important to interpret it accurately. The "human factor" should be scrutinized relying on the experience of highly-qualified specialists, since all areas differ from each other by interaction with machines, procedures and the surrounding environment, as well as cooperation of people inside these areas.

The study of the methods revealed their advantages and disadvantages for further synthesis and optimization. The main task was to improve the most suitable method, which will have the maximum number of affecting factors. The experimental method is highly accurate, but it requires high costs to work on analogues for each specific type of fasteners. The calculated method based on a single experiment allows to determine time standards for various fasteners. The given method does not require high costs for experiments, but like the experimental method, does not take into account performance degradation with continuous operation time. This leads to serious errors in obtaining time standards for a large number of fasteners. The article shows the optimized model of calculated method, based on a linear approximation of dependence of the number of fasteners replacements (removals/installations) on time at multiple intervals. The optimized model allows to obtain time standards of typical fasteners replacement with different geometric characteristic taking into account performance degradation over time. Several experiments on the aircraft were conducted for testing the improved calculated method. On the basis of the experimental data the researchers built graphs of the number of fasteners replacements (removal/installation) on time with different geometric characteristics taking into account performance degradation over time. The data obtained is advisable to use for calculation maintainability factors on aircraft design stages. Program realization of these methods and systematization of the received time standards allow to improve maintainability, due optimization number and position of airframe fasteners and systems units and aviation equipment for the aircraft being designed and modernized. Application of the automated systems of design and analysis will contribute to labor input decrease at the aircraft maintainability analysis.

The article suggests a new type of the parachute system (PS). Its distinctive feature is the presence of an elastic link (EL) for attaching the cargo to the parachute, and the cargo itself is divided into two parts, m1 and m2, comparable in weight and suspended one under the other. The cargo is connected by a cable through the cable length control mechanism. PS in flight consists of a parachute, stretched EL, cargo m1, the cable length control mechanism, cable, cargo m2. The main feature of this type of PS is the ability to provide low dynamic overloads of m1 cargo during the entire flight, including landing. For a soft landing of m1 cargo, it is necessary to choose the main parameters of the PS correctly: the parachute area, the EL stiffness, the weight of m1 and m2 cargo, the length of the cable. To confirm the efficiency and feasibility of the proposed concept, an experimental PS with a flight mass of m ≈ 10 kg was designed, prepared and tested. The parachute is made of zero porosity fabric, its area is S = 2.2 m² It has a cylindrical skirt that is used to give stability to the PS in flight. As an EL a silicone tube is used with the length of l₀ = 6 m when unstretched, but in flight under the weight of cargo ml and m2 it is stretched to l₀ + Δl ≈  17 m. The mass of the cargo ml is m₁ - 5.5 kg, m2 cargo has a mass of m₂ ≈  4.5 kg. To raise the PS a two-seat hang-glider was used. The drop occurred from the height of H ≈  200 m. The rate of decent before landing was Ve = 8...9 m/s. The analysis of the final records of dynamic overloads shows that during the entire flight, including landing, the total cargo overload ml did not exceed n = 5. Thereby operability, feasibility and the declared properties of the offered type of PS are confirmed.

Automatic dependent surveillance of broadcasting type (ADS-B) is an important means of ensuring the safety and efficiency of air traffic. In the future, the role of ADS-B will increase. At the same time, the cyber security of ADS-B is clearly insufficient. The article analyzes the problem of low security of ADS-B. The main reasons for the vulnerability of ADS-B are the system openness and modern achievements in the development of computer technology and software defined radio (SDR).The classification of probable attacks on the ADS-B system with the goals determination, complexity of implementation and damage from the attack is given. It is concluded that other aviation radio-technical systems possess similar vulnerabilities and require a comprehensive solution to the problem of increasing the security level. The main reasons for insufficient security of aviation communication, navigation and surveillance systems are: long development and certification cycles, legacy and compatibility requirements, price pressure, frequency overloads and the preference for open systems. The paper gives an overview of the main ways to improve the ADS-B system security. It is shown that all methods of improving security can be divided into two groups: methods based on the identification and authentication of broadcast radio networks subscribers and methods based on the verification of data transmitted over broadcast radio networks by unidentified subscribers. The methods of the first group implement algorithms of the "identification-authentication" type and can be divided into non-cryptographic and cryptographic; the latter can use symmetric or asymmetric encryption. The methods of the second group are based on various algorithms for data verification from the ADS-B system with some additional data obtained through other channels or other sources. The methods of the second group are considered: multilateration, distance restriction, Kalman filtering, statistical hypothesis testing, group verification, reasonableness check and the use of additional data. The article provides the examples of using some methods to improve the security of the ADS-B system, their advantages and disadvantages.

At present, there is a great interest in the development of new airfoils for wind turbines and high-lift wings of unmanned aerial vehicles (UAV). The requirements for such airfoils differ from conventional aircraft airfoils, because of structural reasons and extreme operating conditions. So, wind turbine airfoils operate frequently under fully separated flow when stall is used for power regulation at high wind speeds. At the same time design of airfoils for wings UAV poses the problem of availability of high-lift at low Reynolds number. Modern airfoils are to a large extent developed from numerical methods. However, the complex flow conditions such as separation at high angles of attack, laminar separation bubbles and the transition from laminar to turbulent flow are difficult to predict accurately. Hence, testing of airfoils at a two-dimensional condition is an important phase in airfoil design. The development and validation of a 2D testing facility for investigation of single and multi-element airfoils in the wind tunnel Т-102 with open test section are considered in this article. T-102 is a continuous-operation, closed-layout wind tunnel with two reverse channels. The test section has an elliptical cross-section of 4 ×2,33 m and a length of 4 m. Two big flat panels of the L × H=3 ×3,9 m size installed upright on balance frame aligned with the free stream are used for simulating two-dimensional flow in the tunnel test section. The airfoil section in the layout of a rectangular wing is mounted horizontally between flat panels with minimum gaps to ensure 2D flow conditions. The aerodynamic forces and pitch moment acting on the model were measured by wind tunnel balance. To determine boundary corrections for a new test section of wind tunnel, the experimental investigation of three geometrically similar models has been executed. The use of boundary corrections has provided good correlation of the test data of airfoil NACA 6712 with the results obtained from the wind tunnel except for lift and drag coefficient values at high angles of attack.

The paper presents the influence of the vortex flow features, in particular, the phenomenon of vortex burst on the longitudinal and lateral aerodynamic characteristics of the maneuverable aircraft model with a sharp-edged fore-body. Numerical simulation of vortex flow has been conducted at low subsonic speeds (M = 0.15) in a wide range of angles of attack α = 0 ÷ 35° at zero sideslip β = 0°, as well as at fixed values of angles of attack a = 10,25,30,35° in a wide range of slip angles β = 0 ÷ 20° using k - ω SST turbulence model with curvature correction due to the insensitivity of the standard model to such effects. A satisfactory agreement of the numerical results with the experimental data on both longitudinal and lateral aerodynamic characteristics in a wide range of angles of attack and sideslip is obtained. According to the results of the numerical simulations, all the main nonlinearities in the integral characteristics associated with the vortex breakdown phenomenon and the interference of vortex structures were explained. The physical features of the vortex flow around the maneuverable aircraft model with a sharp-edged nose and their influence on the longitudinal and lateral aerodynamic characteristics are revealed. The phenomenon of vortex breakdown significantly affects the aerodynamic characteristics of the model. And with the increase of the angle of attack the point of vortex breakdown moves up the stream. At non zero sideslip vortices are destroyed asymmetrically, which leads to a loss of transverse stability of the model. The interaction of the nose and wing vortices, as well as the relative position of the points of vortex breakdown in the range of angles of attack 18° < α < 28° at zero slip angle lead to nonlinearities in the dependence of the lift coefficients and the longitudinal moment of the angle of attack. At large angles of attack, the main vortices forming from the sharp-edged nose make a major contribution to the change in the aerodynamic coefficients, in contrast to the round nose, where the yawing stability is often determined by secondary vortices. The phenomenon of vortex breakdown significantly affects the contribution of the sharp-edged nose to the yawing stability. Moreover, its effect can be radically different at different angles of attack (a = 25-30° and 35°). The local change in the contours of the fore-body in the plan view also significantly affects the directional stability due to the delaying of the vortex burst.

The disadvantage of (RLI) radar images obtained with a single-channel radar station is the presence of speckle that leads to intensity flashes increasing the number of false alarms when detecting point targets. Therefore, the detection and target distinguishing by their reflective capability (using the energy characteristics of the signal) is not effective enough. In polarimetric radar stations the formation of each image element is carried out by the output signals of four receiving channels. Joint processing of these signals allows minimizing speckle without reducing the resolution capability. The paper presents the results of the computer simulation of the suppression methods of the image speckle obtained in the polarized radar stations with the synthesized antenna aperture. The first one uses the norm of the backscattering matrix as a parameter of the intensity of the reflected signal resolution from the i-th element. The incoherent addition of the intensities obtained by sequential overview of the space with several rays is carried out in the second one. Both of these methods can be applied together. The block diagram of such processing for one strip of range is given. The computer simulation of the three-rayed suppression method of the image speckle obtained in the radar stations with the synthesized antenna aperture is carried out. As a model of the reflecting surface a random diffraction grating formed by a set of independent reflectors located at the nodes of a regular rectangular grid with a step of 1 m is chosen. In this connection the image of the grating is formed as an incoherent sum of three images obtained at different angles. The results show that the speckle effect reduces even at angular changes of the order of degree units.

The processing of the elliptically polarized reflected signal in the Earth remote sensing systems makes it possible to obtain additional advantages when solving problems of recognition of the observable objects on the ground and under the ground. Full polarization reception implemented in radar stations with digital synthesis of the antenna aperture when remote sensing of the Earth increases the information content of such radars (the radar image of the investigated surface is detailed, the contrast of objects in the field of view is improved, and various negative effects of the image are minimized). The paper considers the quadrature processing of the reflected elliptically polarized signal in radar stations with digital synthesis of the antenna aperture in the mode of lateral survey of the terrestrial (water) surface. The processing of the reflected signal using the methods of radio polarimetry opens new possibilities for such radars while solving problems of remote sensing of the surface and recognition of radar targets. In addition, radar stations with digital synthesis of the antenna aperture with processing of an elliptically polarized signal have a higher interference immunity compared to radars, where a linearly polarized signal is processed. In the article, mathematical modeling is performed in the part of demodulation of the in-phase and quadrature components of the trajectory signal when the geometric parameters of the polarization ellipse change. The obtained analytical expressions allow estimating the influence of the geometric parameters of the polarization ellipse on the trajectory signal being processed. It is analytically confirmed that the angle of ellipticity affects the energy characteristics, and the orientation angle of the polarization ellipse introduces an additional phase shift in the characteristics of the trajectory signal being processed. Not taking into account these nuances while designing digital units and systems of such radars can lead to the loss of all the benefits of processing an elliptically polarized signal. The paper presents a structural scheme of the polarization radar station with digital synthesis of the antenna aperture.

Aerodrome-enroute surveillance radar systems (ARSR) of civil aviation are designed for detection of aerial objects and determination of their range and movement parameters. Meanwhile, the reflector-type antennas are still the main type of_used antenna systems. Radars (ARSR) have, as a rule, antennas with a bidirectional beam, structurally reflector-type antenna is made in the form of a truss welded structure. The use of active phased antenna arrays (APAR) is a promising direction of radars (ARSR) development. Radars (ARSR) based on the phased antenna arrays can significantly improve such critical tactical and technical criteria as: the accuracy of the coordinates determination, the number of simultaneously followed targets. However, the use of APAR does not solve one of the main problems - the presence of a support-rotary device in the radar (ARSR). The principal necessity of a support-rotary device leads to the need of the use of movable joints of feeder lines, which, with a significant number of antenna elements used in the PAR, significantly reduces the potential time before failure. It seems promising to use in the radar antenna systems based on several stationary multi-beam dual-reflector antennas made by axially asymmetric scheme. Methodology of estimation of aberrations of a dual-reflector sensimetrics antenna based on a polynomial expansion of the eikonal function in the plane of the aperture of the main reflector is proposed in the article. Analytical expressions of the functions of display and rotation of the scanning plane of a dual-reflector axially asymmetric antenna with arbitrary parameters, designed based on clippings from centrally symmetric surfaces of rotation of the second order, are obtained. It is shown that the aplanatic antennas lose their scanning features during the transition to the axially asymmetric variant.

The creation of methods for the study of nonlinear phase systems has a long history, since the 60s of the last century (V.I. Tikhonov, V. Lindsay, M.V. Kapranov, B.I. Shakhtarin, etc.). By now, rigorous and approximate analysis methods of such systems have been developed. However, most methods are limited to the analysis of low order systems. Only in recent years attempts have been made to create methods, which allow to carry out the analysis of high-order phase systems. The material of this article deals with these methods. The article considers the construction of solutions of phase systems on the example of phase-locked frequency of arbitrary dimension with piecewise linear approximation of the nonlinear function. This approximation allowed to use an explicit form of solutions in the linearity and to obtain analytical conditions for the existence of various types of system behavior. The analytical conditions for the existence of solutions leading to the emergence of complex limit sets of the trajectories of phase systems and their bifurcations are obtained. These are homoclinic trajectories in the case of the saddle-focus equilibrium state, which play a decisive role in the occurrence of chaos. It is also shown that it is possible to obtain analytical conditions for the bifurcation of the birth and the existence of multi-pass rotational cycles in a piecewise linear phase system, on the basis of which a criterion for the transition to chaos through bifurcations cascade of doubling the stable cycle period can be obtained; in accordance with the Sharkovsky theorem it ends with the bifurcation of the cycle birth of the period three and the occurrence of developed chaos. It should be noted that the research methods of piecewise linear systems described in the paper were applied by the authors not only to phase systems, but, for example, to the Chua system, allowing various chaotic behavior.