Volume 16, Nº 1 (2015)

Creating and using logical classification algorithms are based on revealing patterns in the input data, and a decision function is formed from a set of these patterns. Search for patterns can be viewed as a combinatorial optimization problem. To produce the most effective solutions, the choice of the optimization algorithm should be made on the basis of the characteristic properties inherent in the considered optimization problem. In this paper we consider some properties of optimization problems that are solved in the course of finding logical patterns in the data. We consider the recognition problem for objects described by binary attributes and divided into two classes. Regularities are the elementary blocks for construction logical recognition algorithms. The problem of finding the maximum patterns can be written in the form of a constrained pseudo-Boolean optimization problem. We study the properties of the optimization model, which describes the search for logical patterns in the data. Research results show that in the search space there is a set of constancy of the objective function. This hampers performance of the optimization algorithms, which begin the search from a feasible point and leading it to neighboring points, since the calculation of the objective function in the system of neighborhoods consisting of neighboring points, gives no information on best search direction. While solving practical problems of large dimension, this set of constancy may own most of the points of the feasible region. We consider the possibilities of improving algorithms of search for patterns. Experimental investigations were conducted on the real-world recognition problems. Experimental results show that the use of information about the proximity of the sample objects to patterns can overcome the difficulties associated with the characteristic features of optimization problem solved and manifested in the presence of constancy sets. And this allows finding the best patterns in the data to use them in solving the recognition problems.

Different purposes gears characteristics studies during the design phase make possible to evaluate the design decisions quality. With use of the standard design approach based on state standards it is often unable to find the optimal design solution. The major problem occurs in the high-precision drive systems design based on the use of the wave gear drive as a drive output unit for the military and aerospace industry needs. In the paper a gears design methodology based on transmission geometric parameters selection and its characteristics analysis with finite element method was presented. Within the framework of wave gear torsional stiffness study, the wheel rotation angle relative to the flexible wave generator according vs. output torque diagram was presented. For cylindrical gears as a component of spacecraft drive as a fast and intermediate stage, impact assessment of selected geometric parameters on the transmission accuracy and load capacity was estimated. A modern manufacture methods review of gears designed by the proposed method with the use of rapid prototyping was present. The trial print results by means of rapid prototyping fine-grained spur gear with involute profile, made of stainless steel and titanium oxide was present. The current level 3d printing development can’t be obtained a quality of teeth side surface is required for special application high-precision drive systems. The overhaul results can be recommended for use in multi-stage gear units designing. The finite element methods usage will provide a visual stresses and strains distribution diagram of drive components at the design stage. The presented technique along with modern methods of gear technological implementation allows you to design not only the precision actuators for special purposes, for the needs of the military-industrial complex or the space industry, but also be used to analyze a wide range of general engineering programs.

Sandwich plates with free edges are widely used in modern aerospace constructions making power base of non-hermetical spaceship bodies. Fundamental frequency of sandwich plate is very useful for weight efficiency assessment of construction that is significant in engineering calculations. The article deals with the problem of fundamental frequency calculation for rectangular sandwich plate with free edges and all corners simply-supported. The plate has symmetrical sandwich package structure consisting of two identical face-sheets and orthotropic core. In this formulation the problem has no analytical solution yet. This is due to the necessity of exact satisfaction of static boundary conditions on free edges of the plate; which is very hard to do. In the article the authors provide an analytical solution of the problem, where the sandwich plate model is based on Reissner-type layered composites theory. Variational equation of plate free vibrations derived from Hamilton principle. Solution procedure uses generalized Galerkin method to solve the variational equation. This method allows applying approximating functions that do not necessarily exactly satisfy static boundary conditions on free edges of the plate, as these conditions are satisfied integrally along each edge. In this paper trigonometric functions are applied as approximating functions. For the case of plate with four corners simply-supported, trigonometric functions give good accuracy in approximation of plate deflection and rotation along the corresponding coordinate axis. The result of generalized Galerkin method implementation is a system of homogeneous linear algebraic equations and then, an analytical formula for fundamental frequency derives from the condition for the nontrivial solution existence of the system. Fundamental frequencies are calculated using this analytical formula for several variants of plates with different combinations of plate dimensions. Verification by fundamental frequency calculations for the same plates in finite-element package shows very good correlation with obtained analytical formula results. Thereby, resulting analytical formula for fundamental frequency could be successfully used in engineering and design calculations with minimal computational cost and enough accuracy.

The importance of engineering data - intellectual property of the company, from management which determines the effective activity of all its services is emphasized. The principles underlying the creation and processing of paper documentation as a common form of presentation of the results of the design are considered. The attention was drawn to a significant inconvenience when working with paper original design documents and the need for specialists in online access to engineering data developed products. The method of transition to electronic originals is offered. In this case, the issuance, negotiation, store design documentation and amendments are made in electronic form. This technology is supported by the regulatory framework and the main provisions of the concept of Informatization of the Russian Federal space Agency, aimed at implementing large-scale projects to create high-tech products. Designed and implemented at SC “SIC “Polyus ” automated control system engineering data and production at all stages of the product life cycle are presented. The strategic principles of the unified information space for engineering data management, describes the mechanisms of effective interaction of several companies ‘Roscosmos’ when working with technical documentation in the framework of the joint development are set out. Interested companies are jointly proposed to continue SC “SIC “Polyus” project on the development and implementation of automated systems engineering data management and production. The basic decision of SC “SIC “Polyus” delivers open source and enterprise-participants on their own with the support coordination services extend the functionality of the system, thereby developing the project to the level of industry solutions.

We consider the problem of identification and control of a sequence of objects in conditions of incomplete information. Among the series-connected objects there may be objects both dynamic and inertialess with delay. This kind of process chains often takes place in the aerospace industry. They arise in the manufacture of rocket technology, electronic products, etc. The problem of integrated management of technological process group certainly belongs to the category of topical. This raises a whole range of problems of identification and control due to the fact that a priori information about them can be different. Below we consider the cases when the a priori information about the object has both parametric and non-parametric nature. We study the problem of identification in non-parametric or part non-parametric uncertainty. If a priori information is not sufficient for the initial statement of objectives, it is natural to use the theory of adaptive learning systems. The main purpose of the following paper is to give an algorithmic framework for modeling and process control within the production schedules. First, we consider the problem of identification and control for a local object, and then the task of managing a group of similar objects. Depending on the particular problem and a priori information level the corresponding modeling and control algorithms are designed. These algorithms are based on enough developed parametric and nonparametric theory of adaptive system. The theory of non-parametric systems is based on local approximation method, in particular nonparametric estimation algorithms of various kinds of dependencies on the results of the input-output variables of the object. The paper presents the specific nonparametric model of inertialess objects with delay and corresponding nonparametric control algorithms with memory. Control devices in this case are devices with memory, which makes nonparametric control algorithms with active accumulation of information the dual control algorithms.

The article discusses theinterference ofelements of the automatedcontrol system.We study thesafety and survivability. Gradationfailure is given. The consequences of failurecells and modulesof the system, causingfailures of other cells and modules, the possibility of preventing thesefailures are highlighted.A range of possibledependent failures is provided. It is shown thata possible source ofdanger can be asmodule failure, and failureof backupelements in these modules. It is postulated that the increase in the number of redundantelements at least does not reduce to zerothe potential danger. The variouslogicalstructures of the compoundelements in ACS are discussed. A typical structureof reliabilityof automated control systemthat performsseveral functions, the tree structure is shown. It is deducedthat one systemAPCS performs several functions. Onespacecraftoften performsseveral functions.Also there are functions of the ACS which do notaffect theoperation. Andto determine the reliabilityof the system wemust determine which elementsinvolved in performing anyfunctions. It is necessary to determine thesequence of elements to perform a functional task. It is illustrated by the development of failures in multi-functionalsystems, the mutual influence of elements in them in case of simple linear andbranchedredundantstructures. We consider the negative effects of redundancy.An example ofcalculating thereliability of the systemwith a parallelconnection of elementsinto accountand dependent failures caused by the elements is given. The conclusion of necessity of non-redundant methodsto improve reliabilityand hazard prevention was made.

The object of the research is the formation principle of the pulsating movement mode for control of the electric drive of the antenna of the radar station of the sector review based on the phase modulation of power voltages of the two-phase asynchronous engine with interruption of one of them in time points when the electromagnetic moment crosses zero. The purpose of the given research is to receive the estimated ratios that make it possible to establish connection between the output parameters of the electric drive and parameters of the executive engine, power supplies and loadings in case of the potential phase shift keying. The authors of the article developed the method of calculation of the electric drive with the pulsating law of movement based on the solution of system of equations in the operating form that are to describe the generalized electrical machine by using Cramer’s method concerning currents of phases of the asynchronous engine. Using the received currents of phases of the generalized electrical machine, the electromagnetic moment is calculated. The next step is that the starting and damping components are singled out from the electromagnetic moment. Then the motion equation permitting to connect the received currents with the output parameters of the electric drive is solved. To solve the motion equation concerning the relocation of a mobile element the method of harmonic balance is used. As a result of researches engineering estimated ratios which permit to establish the correlation between the electromagnetic, starting, damping electric drive moments, speed, relocation and parameters of the executive engine, power supplies and loadings in case of potential phase shift keying are received. In the article the comparative analysis of results of the analytical solution and mathematical simulation of the electric drive is provided in a software environment of MATLAB. On the basis of the performed analysis the authors of the article come to the conclusion that the discrepancy between the currents of the phases of the asynchronous engine received as a result of the calculation and the results of mathematical simulation of the electric drive doesn't exceed 2 %. In turn, the discrepancy between the results of the calculation and the mathematical simulation for the electromagnetic moment and the relocation of a mobile element of the electric drive doesn't exceed 3% and 6% respectively. The authors of the research also stress that the high accuracy of convergence of the results of the calculation with the results of the simulation allows us to speak about competency of the application of the received calculation procedure for determining the output parameters of asynchronous electric drives with the pulsating law of movement.

A fuzzy classifier is one of the intelligent information technologies allowing the generation of a fuzzy rule base suitable for interpretation by human experts. For a fuzzy classifier automated design the hybrid self-configuring evolutionary algorithm is proposed. The self-configuring genetic programming algorithm is suggested for the choice of effective fuzzy rule bases. For the tuning of linguistic variables the self-configuring genetic algorithm is used. A hybridization of self-configuring genetic programming algorithms (SelfCGPs) with a local search in the space of trees is fulfilled to improve their performance for fuzzy rule bases automated design. The local search is implemented with two neighborhood systems (1-level and 2-level neighborhoods), three strategies of a tree scanning (“full”, “incomplete” and “truncated”) and two ways of a movement between adjacent trees (transition by the first improvement and the steepest descent). The Lamarckian local search is applied on each generation to ten percent of best individuals. The performance of all developed memetic algorithms is estimated on a representative set of test problems of the functions approximation as well as on real-world classification problems. It is shown that developed memetic algorithm requires comparable amount of computational efforts but outperforms the original SelfCGP for the fuzzy rule bases automated design. The best variant of the local search always uses the steepest descent and full scanning for fuzzy classifier design. Additional advantage of the approach proposed is a possibility of the automated features selection. The numerical experiment results show the competitiveness of the approach proposed.

Many real-world problems of design and control in a field of the aerospace lead to optimization problems. Such optimization problems are complicated and become a great challenge to many optimization techniques. Moreover, many real-world optimization problems are dynamic and changing over time. Changes occur in the parameters, objectives and/or problem constraints. In this case, search algorithms should have the capability to track moving optima and adapt to a new environment. In past years many approaches for non-stationary optimization were proposed. The best results are achieved using a stochastic population-based search such as evolutionary and genetic algorithms. Unfortunately, real-world non-stationary optimization problems include various types of changes and are poorly predictable, thus there is a problem of choosing a proper optimization technique and tuning its parameters. This study presents a novel approach for designing a multi-strategy genetic algorithm based on a hybrid of the island model, cooperative and competitive coevolution schemes. The approach controls interactions of different genetic algorithms and leads to the self-configuring solving of problems with a priori unknown structure. A short survey on non-stationary optimization problem and methods is presented. The results of numerical experiments for benchmark problems from the CEC competition are discussed. The proposed approach has demonstrated efficiency comparable with other well-studied techniques for non-stationary optimization. And it has significant advantage - it does not require the participation of the human-expert, because it operates in an automated, self-configuring way.

In this paper the problem of a city ecological condition forecasting based on the chemical composition of the air is considered. The procedure of solving this problem with artificial neural networks, grown by evolutionary algorithms is described. Several modifications of evolutionary algorithms and ensemble approach for neural predictor design allowing the increase of prediction efficiency are presented. Also an ensemble method for neural predictor design is considered to increase the efficiency. The existing methods for design of intelligence information technologies ensembles have been considered. The comparison of their efficiency is presented in the paper for a set of test problems. A modified approach for artificial neural network ensembles is proposed, which is different from known before with combined application of existing schemes and methods for ensemble organization. In the problem description the problem of large amount of missing values in the dataset is highlighted. To solve this problem, a modified genetic programming method is applied. The usefulness of this method is shown for the problem solving. The testing shows the efficiency of the presented approach compared to basic and ensemble models. One of the applications of the developed algorithm is the time series prediction. Many technical systems contain a large amount of dynamic parameters, and tracking and predicting these parameters is an important problem. The rocket and space technology is no exception, so the described algorithm is a useful data analysis instrument for it. The developed approach can be used as a method for individual predictors’ creation, and also as way for combining the existing ones. It is shown that this approach allows increasing the accuracy of the resulting models.

The strict hierarchical manpower system is modeled in the state space where the desired number of men in particular rank is determined by predefined trajectory function. The transition model is represented by the principles of System Dynamics where each rank is represented as the state element and transition as the flow. The basis for the model is the structure of the exponential delay chain with additional outflows from particular states. The strategy for achieving the desired states is determined by the application of the genetic algorithms which are implemented in JavaScript as well as the System Dynamics model. Parameter boundaries were taken into consideration which was determined according to the historical data. Predetermination of the desired system states by the set of exponential functions reduced the optimization burden. The optimization problem was defined as the minimization of the sum of quadratic difference between desired and actual states in all ranks for the observed time horizon. Time boundaries in considered optimization problem were not constant which contributes to the complexity of the addressed optimization task. The six state finite automaton code realization is described which prevents the oscillations in the strategies. The algorithm for integration of system dynamics model and genetic algorithm with finite automaton is described.

With the advent of spacecraft designed for long-term operation in space and required constant orientation electromechanical executive bodies on the basis of engine - flywheel began to be applied. It’s happened because total mass of the control device and the equivalent mass (according to the needs power) source of energy (for example solar battery) in this case do not depend on operating period of the electromechanical executive body on the basis of reaction flywheel. At the same time, similar characteristics of control systems with reaction motors increases with the duration of the orientation of the flight. Furthermore, the required amount of inclusions reaction motors that reduces the deterioration of system reliability increases. Therefore, for spacecraft requiring prolonged orientation, application systems with engine-flywheels is more rational. Creating a new electromechanical executive body on the basis of the engine speed managed flywheel system for spacecraft orientation with improved weight and size, will save consumers money when launching spacecraft. The requirement of minimum weight is one of the main imposed on electromechanical executive bodies. The aim of research is to calculate the parameters and develop a design of electromechanical executive body based contactless direct current (DC) motor with improved weight and size characteristics. This is achieved by using a slim stator configured as a printed installation, with the length of the stator cylindrical shape reduced to tens of millimeters of 1,5-2 mm, which involves reducing the size of the power of the valve body, and thus the weight of the entire engine-flywheel. The subject of the research is complex operating characteristics managed by the engine speed - the flywheel provides in the development of the engine-flywheel based on contactless DC motor printed winding on a disk stator. The result of this work is the design of the engine flywheel based on contactless DC motor printed winding on a disk stator.

Engines-flywheels are widely used in the systems of orientation and stabilization of a small-sized spacecrafts. Today the topical issue is reduction of harmful revolting influences on the engines-flywheels caused by errors of manufacturing and assemblage of ball-bearing support, a rotor-flywheel unbalance, electromagnetic influences. Minimization of negative mechanical influences of separate knots and engine-flywheel elements will allow to improve dynamic properties and spacecraft service life as a whole. In presented article principal causes of occurrence of harmful mechanical influences at engine-flywheel work are considered. The methods of their reduction are considered. The short review of existing types of shock-absorbers and principles of their work and described features of application of shock-absorbers for systems of orientation and stabilization on the base of engines-flywheels is regarded. The construction of the shock-absorber for the electric motor-flywheel is offered. The description of work of the developed shock-absorber is achieved. Under the developed drawings the development type of the shock-absorber is made. The technique of carrying out of measurement of vibrating characteristics is made. The conducted tests are consisted of measurement of vibrating characteristics of the engine-flywheel in normal conditions on free elastic pendant without external vibroprotective devices and also together with it. In the article the graphs of comparison of dependences vibrovelocity from frequency of rotation of a rotor-flywheel of the investigated engine on three orthogonal axes without the shock-absorber and together with it are presented. It is revealed, that a shock-absorber installation on a spacecraft a level of vibrovelocity decreases in comparison with level of vibrovelocity on a landing surface of the engine-flywheel. For definition of quantity of this amplitude peak coefficients effectiveness ratio of application of the shock-absorber from frequency of rotation of a rotor-flywheel are calculated. Corresponding graphs show that shock-absorber installation between the engine-flywheel and a spacecraft are reduced a level of vibrovelocity, transferred to a space vehicle to 3,5 - 4 times (on the average in 2 times) and reduces quantity of the harmful revolting moments transferred to a spacecraft. In conclusion, the detention about application of the developed shock-absorber is given.

The influence of surface layer resistance of the solar cell on the output characteristics of the device is considered. The solar cells are widely used in the production of spacecraft solar panels and the efficiency of the solar cell affects the lifetime of the vehicle. Currently, there are significant efforts to increase the efficiency of solar cells (SC). Minimizing resistance of n + -channel allows improve quality of solar cells during prolonged operation, for example in terms of radiation exposure in space. It is therefore interesting to consider more accurate models into account the effect of ohmic losses n + -channel on current-voltage characteristics of solar cells. On the basis of the differential equations for distribution of potentials and currents in a surface n + -layer of n + -p-type solar cells new expression for current-voltage characteristics is received. It has allowed to specify influence of surface n + -layer resistance (R) on output characteristics of solar cells (short circuit current, open circuit voltage, fill factor) in accordance with parameters of n + -p-junction. The simple algorithm of the numerical solution of the specified equations with calculation current-voltage characteristics of solar cells is offered. It is shown, that at the resistance of surface layer R > R n (~ 4 Ω∙cm 2 ) the short-circuit current J SC and the fill factor (η) decreases inversely proportional to , and for R < R n the current-voltage characteristic practically is not depend on R. The obtained results can be used in analysing the operation of spacecraft solar cells.

The article concerns the peculiarities of development of the prospective Russian spacecraft (SC) “Intergelio probe”, with using electric propulsion system as a sustainer. It should explore space around the Sun at close range (60-70 solar radii) and nonecliptic inclinations. The project has to be developed, based on the launch of the spacecraft from the Baikonur Cosmodrome with using “Soyuz-2” launcher and the “Fregat” upper stage. In developing the scheme of flight is assumed that after 5 years the SC has to be injected into orbit with a maximum inclination. Its trajectory is generated using gravity assist from Earth and Venus. The objective of the first phase of the scheme is to maximize flight asymptotic rate approaching the Venus. It is conventionally called “ecliptic”, as the spacecraft trajectory is almost in the plane of the ecliptic. On the second, “nonecliptic”, stage orbital inclination increased due gravity assists at Venus, and for the next meeting the orbit of the spacecraft have to be in the so-called “resonance” with the orbit of Venus, i. e. periods of their orbits must be treated as an integer fraction of the form 1/1, 2/3, 3/4, etc. To minimize the formation of the duration of flight it is necessary to use the orbital resonances of small order. The article discusses three versions of equipment SC “Intergelio-Probe” propulsion: one version with “chemical” engine and the two variants with EPS-based RIT-22 and SPD-140D. In the article the descriptions of these design options is showed. In accordance with these variants flight schemes were developed, allowing the spacecraft to deliver during the active existence of a heliocentric orbit with the required parameters. It is specified the main characteristics of the trajectories. The combined propulsion allows realizing designed trajectory, while providing a full-time operation of science equipment, carrying out correction of orientation and stabilization in the single-component control. This scheme with application of propulsion engine, manufactured by Design Bureau “Fakel”, allows reaching the required parameters of the orbit around the Sun and conducting complex experiments for a specified period of active existence of the SC “Intergelio-Probe”.

This paper refers to thework with the interface of information interchangemultiplex channeldescribed inGOST R52070-2003 and foreign standard MIL-STD-1553B.In introduction authors discuss the interface of consumers, operating in a system of information exchange, and the actualmodules that function as endpointsin onboard spacecraft equipment. Further attention is given to the module which is actively used nowadays. In the article module’smain disadvantages andproblems of using in the spacecraft equipment are specified, the block diagramof the device is presented. The article also presentsthe currentdevelopmentsassociated with the interchange multiplex interfacemodules andterminal devices that carried out in RPC“Polyus”. Thus, the article presentstwo versions of modules, based on ASICN1582VJ2 andN1582VJ3V. The shortcomings of the module, based on ASICN1582VJ2, are given, further eliminated inthe modulebased on N1582VJ3V. Theirstructural andfunctional diagrams are considered, briefly described the principle of operation of the module based on N1582VJ2, and the functioning of the module based on N1582VJ3V is described in more detail. Timingdiagrams of the exchange module logic and the switchingdiagrams of the parallel interface read and write mode to external devices are shown, and the last aredescribed in detail. A photoof the multiplex channel modulebased on N1582VJ3V is presented. Next,the authorspublish the resultsof testing the developed module based on N1582VJ3V against GOST R52070-2003. Theverification ofcompliance to the logical interface protocol, as well as the electrical parameters of the signals, in particular the input and output, is described. The module response to some commands in the formof diagrams is presented and described. The waveformsof electrical signals are shown, and their detailed characteristicsare collected inthe table. In conclusion, the article gives the tabular comparison of the modulesmentioned earlier.In the end, the authors talk about the possible uses of the module in the onboard equipment of spacecraft.

It is known that with increasing fineness of the structural components of the alloys the mechanical properties of the obtained products are increased. It is noted that a sufficiently large parts, components engineering products, produced by the foundry, due to inherent in this method advantages compared with other technologies for the manufacturing of parts, the most significant of which is the relative simplicity of the technology, however, allows to obtain a complex configuration details, which are almost impossible to produce by other methods, while ensuring the required technical documentation characteristics. These details, in particular, are cast parts, which are parts of the components, mechanisms and machinery transport machinery. However, in this industry, especially in aerospace engineering, widespread aluminum die casting alloys has received. In the manufacture of cast parts one of the main ways of improving quality is a modification, the essence of which consists in the introduction into the molten metal substances, which serve either as crystallization centers, or block the growth of emerging crystalline formations. To date, the "chopping" the possibilities of applying the means of modification, has reached its limit. And in recent years for this purpose there are more effective modifiers in the form of nanopowders of refractory high-strength chemical compounds (nitrides, carbides, oxides, borides, and others), the application of which leads to a significant enhancement of the mechanical properties of molded products. The paper presents examples of the application of nanpowders in the manufacture of aluminum alloys castings vehicles, as well as their use during welding, a process which is almost identical with the casting.

The defense industry is traditionally the engine of the Russian economy. In this sphere it is concentrated more than a half of all innovative development existing in our country. Application of the results of researches is possible, in a case of protection of the sovereignty and territorial integrity of the Russian Federation, in national economy civil industries, and for the purpose of sale in the international military and civil production markets. The defensive industry can't exist indifferently, from state control and management. In this regard we need steady instruments growth by means of which realization it is possible to transfer advancing development impulse and at the same time to exercise control of results. No doubt, these tools are innovative projects. However their realization demands accurate classification, for the purpose of a choice the most effective. At the initial research stage post-reform activity indicators of the defense industry enterprises are considered, the financing amounts of the state defensive order are specified. Various points of view concerning the content innovative project are presented. In borders of the real research author's interpretation of this concept in relation to the considered subject is used. The features of the enterprises and innovative projects defense industry complex are marked out. It is raised the influence question of the territory placement of the defensive industry enterprises on processes their steady functioning. The question about innovative projects typology of the defense industry enterprises complex is studied. The authors were faced by a task to develop typology corresponding to features of the defensive industry enterprises. The existing typology of innovative projects, representing the greatest scientific interest is investigated. Classifications sings are studied, the most widespread are allocated. As result, the innovative projects typology at the defense industry enterprises is offered.

The problem of workforce training is a particularly relevant in the aerospace industry, because the aerospace industry is an area where the unique technical systems are created, cutting-edge science is used, breakthrough technologies are implemented. At the same time, last priorities of quantitative growth of import substitution and domestic economy aerospace products are applied to a system of training skilled workers aerospace companies insurance that the competence of working conditions it is a key result of their training. The purpose of this study is to analyze and systematize the types of workforce competences in a single competence typology, taking into account the strategic priorities of the aerospace industry. The objectives of the study are the following: relevance justification of the competence approach to training workers in the aerospace industry; analysis of existing researches in the field of competences typologies; determination of clusters set and types of competences in working typology. The composition of factors which actualize the use of competency approach to workforce training is the following: the awareness need for workers with high “price decision” on a separate workplace; the need for properly evaluation of individual contribution of a specific worker in a unique manufacturing result. (this is connected to the specifics of individual and small-scale production at the aerospace company); inclusion in the evaluation of worker's labor his personal qualities, which provide motivation for productivity increase; high adaptability of competency model in the selection, motivation, evaluation and workforce development. Two approaches are provided to the understanding of competence essence: activity - motivational approach (competence as a willingness to act) and the descriptive approach (competence - a set of employees characteristics). Activity-motivational approach is the most relevant approach to the workforce competences. This approach underlines the willingness and ability to show professional activities as a result of learning knowledge skills. The author analyzed a number of competences typologies of domestic and foreign scholars. The author proposes to typify the working competences as a corporate, personal and professional. This method allows taking into account the most accurate industry-specific during the structuring and typing competences. Moreover, this method will allow us to focus on the certain staff categories including the category of workers.