ВИДИ МЕТРОЛОГІЧНИХ ХАРАКТЕРИСТИК І СКЛАДУ РОБІТ З ЇХ ВИЗНАЧЕННЯ НА ОСНОВНИХ СТАДІЯХ ІСНУВАННЯ КОМПОЗИТНИХ КОНСТРУКЦІЙ АГРЕГАТІВ ПОВІТРЯНИХ СУДЕН ТРАНСПОРТНОЇ КАТЕГОРІЇ

It is shown that the development of the concept of metrological support for the creation of composite structures of aircraft aggregates of the transport category and their support at all stages of the existence of an aircraft should be based on the formation of a complex criterion for the effectiveness of the use of polymer composite materials. It is noted that the effectiveness of a structure made of polymer composite materials is provided by various methods, methods and technical means of metrology. The structure of a complex of studies aimed at developing the concept of metrological support is discussed, the first point of which is to analyze the types of metrological characteristics and the scope of work to determine them at the main stages of the existence of composite structures of aircraft aggregates of the transport category. Based on the analysis of numerous publications on the problem of metrological support of the main stages of creating technical products, the main types of measurements of the metrological characteristics of composite structures of aircraft aggregates of the transport category have been established, and the composition of the nomenclature of works on metrological support of the main stages of the existence of these structures has been determined. 12 main types of measurements of parameters have been identified, on which the whole variety of production physical quantities and the description of the properties and characteristics of structures of aircraft aggregates made of polymer composite materials are based. The composition of the main works on the metrological support of the four stages of the existence of the aircraft is revealed: design, production, operation and disposal of composite structures formed into systems of sequential blocks for performing these works. It is shown that the tasks of metrological support at the facility manufacturers should be solved during the technological preparation of serial production and testing of the installation series of products, and also take into account the peculiarities of aircraft operation and disposal of composite structural elements in terms of work safety and economic efficiency of their results. An enlarged sequence has been established for organizing work on metrological support for measuring the properties of composite structures of aircraft aggregates at aviation enterprises. The results presented in the first approximation provide a solution to practically important aspects of the problem under discussion.

ОСОБЛИВОСТІ ЗАСТОСУВАННЯ МЕТОДІВ ФІЗИЧНОГО МОДЕЛЮВАННЯ ДЛЯ АНАЛІЗУ ПРОЦЕСУ ПРИЗЕМЛЕННЯ ПАРАШУТНИХ ПЛАТФОРМ НА НАДУВНІ ПОВІТРЯНІ АМОРТИЗАТОРИ

Research has been carried out aimed at developing the theoretical bases of physical modelling of landing processes of parachute platforms on inflatable air shock absorbers. At the same time, the features of the application of physical modeling methods for solving this task are considered. The conditions, landing features and operation of parachute platform devices at landing on inflatable air shock absorbers are determined. It is shown that presently parachute-depreciation systems have become widespread, in which soft tissue shells are used, filled through the inlet openings with atmospheric or air injected from gas bottles air. The operation of these devices is based on the compression of air in the shell and expiration of him through exit holes (valves). At the same time, air inflatable shells absorb the kinetic energy of the impact, controlling the release of air through exit holes.It has been established that the most effective method for studying the behavior of a dropped vehicle is physical modelling, which uses a free-flying dynamically similar model (FDSM) or stand dynamically similar model (DSM) of a dropped object as an research object. Modeling of landing processes of parachute platforms on inflatable air shock absorbers is not related to the dynamics of the flight and air flow around surfaces. Therefore, for this task, the existing developments in physical modelling of dynamics flight cannot be applied, and for the theoretical substantiation of the dynamic similarity to modeling motion, it makes sense to use the laws of gas dynamics in regard to air shock absorbers.

АНАЛІЗ КОНСТРУКТИВНО-ТЕХНОЛОГІЧНИХ ОСОБЛИВОСТЕЙ ЛОПАТЕЙ НЕСУЧИХ ГВИНТІВ ВАЖКИХ ТРАНСПОРТНИХ ВЕРТОЛЬОТІВ

The analysis of the design and technological features of the rotor blades of heavy transport helicopters is carried out. The main performance characteristics of heavy helicopters are presented. General requirements to helicopter main rotor blades design and specifications for their production are formulated. The design and force diagram of heavy helicopter main rotor blades is considered. The features of structural materials for the main rotor blades of heavy transport helicopters are marked. The main rotor blades differ in their design due to different approaches to materials, manufacturing and layout of blade elements. The main rotor blades of an all-metal design, for design and technological reasons, are divided into two groups: a frame structure with a tubular steel spar and an aluminum extruded spar. As a result of a number of design and technological measures the service life of the main rotor blade of helicopter Mi-6 was brought from 50 hours to 1500 hours. The principal peculiarity of the steel tubular spar of the main rotor blade of the Mi-26 helicopter is the absence of the shaft lug. The features of mixed design main rotor blades are presented. The method of parametric modeling of helicopter main rotor blades is presented. The application of the three-dimensional parametric models of structural elements in practice of designing and construction enables to perform numerical calculations of aerodynamic and strength characteristics both of separate aggregates, units and details and of the helicopter as a whole by means of the finite element method. The method of parametric modeling of the main rotor blade of the transport helicopter with the computer system CATIA V5 is a modification of the method of integrated designing of the elements of aviation constructions. Parametric master geometry of the main rotor blade is a linear surface, created by basic profiles of the blade. On the basis of parametric master geometry a space distribution model is created that determines the position of axial planes of the power set of the blade for further creation of the blade detail models. Technological flowchart of main rotor blade manufacturing is presented, manufacturing and surface hardening technology of steel tubular spar is considered. The technology of manufacturing and molding the nose part of the blade of the main rotor mixed design. The technological features of slipway assembly-gluing of the main rotor blade are considered, the content of off-slipway work is given.These materials can be useful in theoretical and experimental studies to extend the service life of the rotor blades of Mi-26 helicopters, which are currently in operation in Ukraine.

ПРИНЦИПИ ПРОЕКТУВАННЯ ЛЮДИНО-МАШИННОЇ ВЗАЄМОДІЇ У ЦИФРОВОМУ СЕРЕДОВИЩІ

Modern society life is inextricably linked with the digital environment. A consequence is the transformation of ergatic systems into digital ones. The result is the emergence of new types of man-machine interaction. The essential feature of such interaction is to minimise human involvement in the ergatic system functioning. According to this, the issues of organising the safe and effective functioning of digital ergatic systems have priority importance. In this regard, the aim was to study the features of man-machine interaction in an actual digital ergatic system. We chose an ergatic system for research. The main elements of the system were students (70 people of the first-year study) and teachers (5 people) of the Simon Kuznets Kharkiv National University of Economics, as well as the digital system “Personal training systems the Simon Kuznets Kharkiv National University of Economics” (PTS). This digital system is an adapted model of the Moodle digital system. The study found out that the key components that determine the safety and efficiency of the digital ergatic system are the operator's digital mindset, digital tools and digital devices. The study of these components in the system made it possible to establish that it had a balanced state. It is substantiated the optimal form of man-machine interaction in the system. It is mixed learning. It is shown that the tendency to minimise the human role in a digital ergatic system does not always have the expected positive result, which determines the need for further research on this issue. In addition, we analysed the difficulties arising in the design of digital systems. The main reason for this is a lack of developers awareness of the ergonomic and cognitive aspects of man-machine interaction. It is shown that the development of critical thinking and intuition in students is closely related to the individual trajectory of learning. For this, it is essential to update interdisciplinary knowledge. In this case, it is necessary to familiarise students with current concepts and system-forming principles, which are the basis of human factors engineering. It was substantiated that the application of current concepts and system-forming principles in training will allow optimising man-machine interaction. The positive results will be evidence even at the stage of designing digital systems

ГЕНЕЗИС ЦІЛЕЙ І ЗАВДАНЬ ВИБУХОВОГО ШТАМПУВАННЯ (ДО 70-РІЧЧЯ ОДНІЄЇ З НАУКОВИХ ШКІЛ ХАІ)

The paper is devoted to development of one of the scientific schools Kharkiv Aviation Institute (Now National Aerospace University named after M. E. Zhukovsky “KhAI”). This school was born after World War II quite hard after period of National economy restoration and now it continues to develop during last 70 years. The article deals with the origins and genesis of objectives and tasks formulated for think tank and followers during dozens of years. Influence of the world geopolitics on development of mentioned scientific school and reached results is shown. From relatively primitive goals and tasks formulated by R. V. Pikhtovnikov in 1949 up to complicated problems of controlling of impulse energy flows to get high-precision large-dimensional sheet articles. From development of simple manufacturing process conducted in field conditions up to creation of up-to-date manufacturing complexes with correspondent buildings, equipment and technological jigs.Paper draws attention that successful development of scientific school and international expansion of labor market were stipulated by governmental support, both financial and organization ones. Paper shows results of technological systems development. Defefinite analogy with development of biological systems can be observed, i.e. evolution from the simplest to more complicated under influence of external factors.One has to note that paper deals with development of only one direction of scientific school, i.e. sheet articles forming. Research and development of such two other directions as impulse forming by impact of solid and impulse volumetric forming are waiting for their researchers. Authors of the paper tried to escape of conventional approaches of scientific schools description and concentrated on studying of objectives and tasks occurred in frames of considered scientific school. Therefore, the paper doesn’t mention many names of scientific advisors of different directions, titles of exact studies and topics, which involve crucial contribution in achievements of mentioned scientific school.

АНАЛІЗ МОЖЛИВОСТЕЙ РЕАЛІЗАЦІЇ МОДУЛЬНОГО ПРИНЦИПУ СТВОРЕННЯ МОДИФІКАЦІЙ ПОВІТРЯНИХ СУДЕН ТА ЇХ ЕФЕКТИВНОЇ ЕКСПЛУАТАЦІЇ В СИСТЕМІ ВІТЧИЗНЯНИХ АВІАПЕРЕВЕЗЕНЬ

It is known that an aircraft generates income for the operating airline only when it is in the air. Being on the ground, at the airport, airlines incur high costs for aerodrome maintenance of the aircraft. The longer the aircraft is stationary on the ground, the shorter the actual flight time of the aircraft. In this regard, the possibility of implementing one of the promising principles for the creation and effective operation of modifications of aircraft of the transport category - the modular principle - has been analyzed. The prospects for the implementation of modular modifications in domestic airlines in the context of further development of the market economy are considered. Modifications based on the implementation of the modular principle are classified into two types - created in the form of autonomous modules placed in the fuselage during aircraft operation and in the form of a removable modular compartment of the aircraft fuselage. A review and analysis of existing projects of these types of modular constructive and technological solutions, a comparison of their advantages and disadvantages in the technical and economic aspects of the prospects for their feasibility are carried out. The possibility of effective implementation of the modular principle of modifications of aircraft of the transport category was assessed, for which a generalized analysis of domestic and foreign information related to the state of the problem under discussion was carried out, on the basis of which an enlarged block diagram of a comprehensive methodology for analyzing the efficiency of operation of modular modifications in the air transportation system was synthesized in comparison with traditional (existing). The key aspects of the content of the main blocks of the scheme are revealed, including the main provisions of the maintenance and repair of aircraft in modern conditions of their operation, based on foreign experience, as well as the main aspects of the content of the blocks for accounting for weight losses in the design and implementation of traditional and modular modifications of aircraft. The generalized information related to the implementation of the synthesized block diagram, focused on subsequent addition, should form the basis of compliance methods and regulatory documentation in the design and implementation of promising domestic modifications of aircraft of the transport category.

АНАЛІЗ СУЧАСНОГО СТАНУ РОЗВИТКУ БЕЗПІЛОТНИХ ЛІТАЛЬНИХ МІКРОАПАРАТІВ МУЛЬТИКОПТЕРНОГО ТИПУ

The development of unmanned aerial vehicles is of great interest to both the largest aircraft companies and design enthusiasts, and among the total volume of developments, the volume of multicopter unmanned aerial vehicles occupies one of the leading positions. In this regard, the analysis of existing developments and the definition of future research in this direction is relevant. Multi-helicopter drones have a wide range of functions in both military and civilian use.The paper collects and analyzes statistical data of micro-unmanned aerial vehicles of the multicopter type to determine the achievements in the field of design of micro-unmanned aerial vehicles (UAVs). The current classification of UAVs is considered; as a result of the analysis of statistical data its expansion is offered. The take-off and mass characteristics of the micro UAV are described. The tables showing the existing UAVs are given. In addition, the flight characteristics, aerodynamic schemes and type of engine that are most rationally suited for micro-unmanned aerial vehicles according to their purpose and class are determined.Based on the obtained data, a prototype model of a micro-UAV with improved characteristics was built. The model successfully completed all tasks. This indicates that the new UAV "Fear-1" is a successful project and it has the ability to remotely control by phone or any other equipment designed for this purpose. In addition, the designed device can additionally hang in the specified coordinates."Fear-1" confidently performs tasks in automatic mode, as well as independently decides to return to the starting point of takeoff, if: there is a loss of communication, the battery level has reached a certain level, the UAV has completed its task or used more miles -amperes than specified by the output parameters. The drone has the ability to fly in "Follow me" mode on the selected GPS transmitter. The quadcopter was tested in difficult weather conditions, when the wind force reached 8 points (about 22 m / s). Noise immunity tests were also performed in the industrial frequency range (from 2.4 GHz to 5.8 GHz).

КОМПОНЕНТ ТЕМНОЇ МАТЕРІЇ

A possible component of dark matter is considered. Astronomer began to talk about this matter for a long time, when the speed of movement of galaxies in the clusters was coordinated with classical mechanics. Subsequently, the idea of dark matter became used in the dynamics of stars and lineling phenomena. The observational data of astronomy and astrophysics indicate another path, which leads to the idea of the existence of dark matter, if these data are considered through the prism of the main principles and laws of natural science. On this path, the component of dark matter (DM) appears as an environment in the universe necessary to ensure the life of galaxies. The origin of the dark matter and the functions performed by it are binding to star electromagnetic radiation (SER). Features of the interaction of a two-component system - DM and SER - the basis of all further conclusions. First of all, the outer space is considered filled with subtle forms of matter. It is assumed that DM belongs to them. The presence of two giant material objects distributed over the entire space of the Universe, DM and SER - means their interaction among themselves. First, it follows from dialectic, arguing about the relationship of phenomena in nature. Secondly, from the interpretation of the results of measurements of cosmic microwave radiation obtained by the Arcade system (NASA, 2006). A two-component environment - DM and SER - contains all the baryon matter of the universe, ranging from elementary particles and ending with galactic clusters. Support for "life" of baryon matter is carried out through a number of functions performed by this medium. It is assumed that the star radiation, spreading the space, gives its energy to the dark component. The photons shifted into the microwave region are capable of pairing unaging among themselves in counter courses and small sighting distances. Appearing bosons particles correlate with dark matter. These particles have zero spin or two. Their spectrum of mass turns out to be continuous, the maximum mass of the particle is given. The assumption of energy transmission by a quantum dissemination environment and the microwave hypothesis is consistently explained by many observation results. First of all, it is a red shift in galaxies spectra and the presence of a large cosmic microwave background with its intensity variations at relatively small time intervals. DM particles due to the gravitational interaction return the energy back to its baryonic sources. At the same time, the dark component additionally fills the central supermassive object of the galaxy, which in the quasar phase conducts utilization of star waste with hydrogen regeneration. It is DM that provides large energies allocated by quasars. Given the small part of the star matter, turning into the SER, it is shown that the particles of DM are a medium with a relatively low temperature. It is concluded that DM and SER are a comprehensive dynamic environment in which the baryon matter of the universe lives and develops. Through this two-component "ocean" of matter, all major metabolic processes supporting the "life" of galaxies are carried out.

МОДЕЛЮВАННЯ ПРОЦЕСІВ ВИРУБКИ-ПРОБИВКИ ПЕРЕДАВАЛЬНИМИ СЕРЕДОВИЩАМИ

During improvement of the quality of products and reducing its cost, sheet metal stamping production, being the basis for the aerospace industry, should more intensively introduce modern production technologies, especially design. There are a large number of factors influencing the stamping process (especially parts with complex geometry), more comprehensive consideration of which would allow to optimize such processes, thereby reducing the manufacturing cost and improving the quality. Currently the processes of forming and separation of complex parts by of an elastic pad are of interest from the point of view of optimization and the final determination of the nature of the behavior of the material. This includes the refinement of such parameters as the maximum permissible thinning, the strength of the die. Clarification of these and other parameters will significantly reduce energy required. Determination of these and other parameters of sheet metal stamping is possible due to application of the modern analysis methods. For numerical studies in the sheet stamping production, the variational method or FEM is the most suitable. Computer modeling makes it possible to investigate the behavior of the material, the kinematics of the workpiece movement during forming process, select the correct loading scheme for the workpiece, and also makes it possible to consider several options for the location of the workpiece in the die, which is very important for stamping thin sheet metal blanks. It provides a significant reduction of the time and costs for carrying out natural experiments, and decrease of technological preproduction preparation of sheet metal stamping. The development of a mathematical model based on the FEM makes it possible to determine not only the required parameters of the process, but also to consider the forming process during its certain stages, to determine the stress-strain state, indicating at the same time the problem zones of excessive thinning, loss of stability, the need to apply a die with a back pressure for cutting of thin sheet metal blanks. It allows to evaluate the quality of a ready product according to the calculated parameters, to use the results obtained for the design of elastic pad

ОЦІНКА ВПЛИВУ ЦЕНТРУВАННЯ НА АЕРОДИНАМІЧНУ ЯКІСТЬ, ПОЛЯРУ І ДАЛЬНІСТЬ ПОЛЬОТУ ЛІТАКА

The method of transport category airplane flight range estimation taking into account its center-of-gravity position variation in the process of fuel utilization at cruising flight mode is presented. The method structure includes the following models:– Interinfluence of main parameters on each other in the process of fuel utilization;– Estimation of CG position influence on lift-to-drag ratio in cruising mode;– Quantitative estimation of center-of-gravity position variation influence on airplane flight range.Simulation of the main parameters is based on authoring researches, establishing interinfluence among geometrical and aerodynamic parameters of wing, parameters of horizontal tail and center-of-gravity position variation caused by fuel utilization in cruise flight. Such model allows estimating airplane center-of-gravity influence on their values and relative position.Aerodynamic parameters variation caused by center-of-gravity shift resulted in necessity to take the influence into account, for required engine thrust variation; that is shown in the publication in the form of dependences allowing to take into account the required thrust variation and their influence on range variation.On the base of interinfluence model and taking into account required thrust variation (with center-of-gravity position shift), lift-to-drag variation has been obtained and analyzed in the form of dependences , for middle airplane of transport category.Expression for estimation of airplane flight range under variable values of its mass and center-of-gravity position is obtained on the base of these models; that allows to increase flight range by means of center-of-gravity position dedicated shift.On the example of mid-range transport airplane, it is shown, that at Mach number and center-of-gravity shift back from to , the increase of flight range makes .On the base of presented models, it is shown, that airplane center-of-gravity position influences lift-to-drag ratio, fuel efficiency and as a result on flight range at cruising flight mode.Application of aft center-of-gravity position allows to decrease engine required thrust (and to decrease fuel consumption), and increase lift-to-drag ratio and airplane flight range.