Vol 17, No 4 (2016)

The problems of image pattern recognition are nowadays solved in many areas - beginning with satellite analysis of the Earth surface all the way to human face analysis in the human-machine interaction systems. One of the most successful algorithms of image analysis and recognition is the convolutional neural network. The back propagation algorithm used for training of these networks belongs to the class of gradient algorithms; therefore it often converges to local minima. In this paper we propose a hybrid algorithm for convolutional network training, which is aimed at searching for global optimum, and consisting of two stages. At the first stage a genetic algorithm is used to search for the subdomain of the search space that includes the global optimum, whereas at the second stage a back propagation algorithm is used to find the actual global optimum. Genetic algorithm includes an internal procedure that maintains diversity of the solutions population, which allows examining the search space more thoroughly and finding various successful convolutional network configurations. The solution found by the genetic algorithm is used at the second stage as an initial approximation of network weights. After that the network is trained using a back propagation algorithm. The developed hybrid algorithm has been tested on the emotion recognition problem; it has been compared to a traditional back propagation algorithm. A comparison was made on the classification accuracy, as well as the F-measure for the emotion recognition problem in two formulations - speaker-dependent classification, and speaker-independent classification. Hybrid algorithm has yielded a better performance according to both criteria, and in both problem formulations compared to the standard algorithm used for convolutional neural network training.

Due to the development of the space industry, expansion of functions of spacecrafts and increasing its service life, matter of its reliability are becoming very important. Therefore, it is necessary to provide a high quality of electronic components in space production and pay attention to the homogeneity of its specifications to ensure a high level of consistency of its work as the part of the device. This requires a complex control system, testing and automatic classification of arriving components, which aims to select components manufactured within the same production batch from providing components. Besides, the results of the selective destroying physical analysis can be extended to all batches of components, only being confident in homogeneity of this batch. This paper is devoted to one aspect of such a system - the definition of the estimated number of production batches in a composite party of components. The task of determination of number of groups is one of the most difficult aspects of data classification. There is significant amount of various criteria for evaluation of expected number of groups in literature today. We studied the effectiveness of various criteria, and concluded that the method based on the Silhouette criterion is very effective to solve the problem of automatic grouping, particularly for grouping of spacecraft electronic components on homogeneous production batches. We paid special attention to the “outliers” - elements, which characteristics are far from the characteristics of the major amount of classified elements. We made experimental verification of the method on real data and showed that the maximum of Silhouette criterion corresponds to the actual number of production batches in the examination selection, representing the combined batch collected from the elements made as a part of several homogeneous production lots. The proposed method for estimating the number of production lots is based on the test data from a specialized test center and does not require additional testing. Thus, this method is suitable for implementation in manufacturing process to improve the quality of spacecraft electronic components without considerable expenses.

In recent years many real-world optimization problems have had to deal with growing dimensionality. Such optimization problems, that are called large-scale global optimization (LSGO) problems, contain many hundreds or thousands of variables and are not separable. Moreover, many real-world problems are usually complex for detailed analysis, thus they are viewed as the black-box optimization problems. Thus, we can use the “blind” search techniques only. The most advanced techniques for LSGO are population-based stochastic search algorithms and are based on cooperative coevolution schemes using the problem decomposition via variables. These algorithms are mainly proposed for the real-valued search space and cannot be applied for problems with discrete or mixed variables. In this paper a novel technique is proposed, that uses a combination of a binary genetic algorithm (GA) and an estimation of distribution algorithm (EDA). The GA is used for solving the main optimization problem, and the EDA is used for collecting statistical data based on the past search experience to provide the problem decomposition by fixing perspective genes in chromosomes. The proposed EDA-based decomposition technique has the benefits of two general LSGO concepts: the random grouping methods and the dynamic learning methods. A standard implementation of the EDA-based decomposition GA and an implementation using the island model for parallel computing are discussed. The results of numerical experiments for benchmark problems from the IEEE CEC competition on the LSGO are presented. The experiments show that the approach demonstrates efficiency comparable to other advanced techniques. At the same time, the proposed approach can be applied for LSGO problems with arbitrary variables as it uses the binary representation of solutions.

Nowadays, there is a stable tendency to reduce weight and size of a spacecraft and, as a result, power supply systems, which are the main service systems. That is why current developments and applications in power systems of power modules with high-performance (weight and size, power, etc.) are essential. This paper discusses the construction of a modular spacecraft power system that provides stable output parameters at the time of its operation both in stationary and in emergency modes. Particular attention is paid to the study of nonlinear dynamic characteristics of the combined voltage converter on the basis of which such a unit can be configured. The bottom line of this study is reduced to find the permissible range of parameters of circuit components, providing a stable single-cycle mode of operation of the device, as well as boundary points of bifurcation, which are points of transition from the single-cycle to high cycle regimes. Thus obtained verifiable mathematical model of the combined converter, based on the switching-discontinuous functions and takes into account the non-linear parameters such as capacitance of input and output filters, as well as the inductance of the storage inductor. The results of a mathematical simulation and experimental study of the combined converter, in particular the bifurcation diagrams of output parameters, dependence of ripples on the load current and gain feedback loop, the output voltage waveform are given. The calculations are checked on a model of such a device, recommendations for practical application of the combined converter in real power system.

Latent heat storage is one of the most efficient ways of thermal control. Unlike the sensible heat storage method, the latent heat storage method provides much higher storage density, with a smaller temperature difference between storing and releasing heat. This paper considers a spacecraft thermal control system based of solid-liquid phase change material for the high heat dissipating component which works intermittently with short duty. Different groups of thermal storage materials, such as metals, inorganic and organic materials are considered. Organic materials are defined as the optimal substances for the thermal control of spacecraft electronic equipment are determined. Most organic thermal storage materials are non-corrosive and chemically stable, exhibit little or no subcooling, are compatible with most materials and have a high latent heat per unit weight. Their main disadvantage is low value of the coefficient of thermal conductivity. The drawback of organic thermal storage materials application due to low thermal conductivity can be successfully resolved by means of parallel arrangement of the hyperheat-conducting plates in the volume of the heat accumulator. Analysis of the use of thermal accumulators with hyperheat-conducting plates as edges for optimal thermal modes of blocks of electronic equipment is presented. The calculation of the basic parameters of the thermal accumulator is performed. Mass of heat storage material, number of edges, spacing between edges depending on the temperature fluctuation amplitude, of the electronic equipment heat and properties of material was determined. On the basis of the solution of the heat equation the calculation of the heat exchange efficiency of edges in the volume of the heat accumulator is made. Higher heat exchange efficiency of the hyperheat-conducting plates compared to copper edges is showed.

In this article, there is a method of calculation of thermal state of chamber of liquid rocket engine of small thrust. There is a physical picture of the processes occurring in the small thrust rocket engine during start and stop moments of motor. The difficulties in modeling the processes during star and stop of small thrust jet engine are presented. The cause is conjugated intra-chamber physically processes occurring at varying parameters during the mixing elements in the off-design conditions. In the article, a mathematical model to predict the thermal state of the combustion chamber for the different modes of engine operation is presented. To simulate the process of starting and stopping the engine applies a quasi-steady approach that replaces the transient process by set of steady-state processes with variable time operating parameters. The initial data for mathematical model is parameters of small thrust rocket engine, developed in Moscow Aviation Institute, working on the components of the nitrogen tetroxide and unsymmetrical dimethylhydrazine, thrust 200 N. The engine is equipped with a separated mixing head, which contains two-component jets, and film cooling by fuel that protects the combustion chamber wall. The results of mathematical simulation of the small thrust rocket engine in the steady pulse modes are given. The pulse modes at 0.05 sec and pause at 0.05 sec, pulse mode at 1 sec and pause at 1 sec and mode, consisting of sets of pulses with different duration are analyzed. The wall temperature of combustion chamber in characteristic sections, depending on the wall temperature by time for internal and external surfaces of the combustion chamber is calculated. The results of calculation for impulse mode approve a large temperature gradient on the internal wall surface of the chamber between pulses are shown.

The increase of available power and the lifetime up to 15 years for modern telecommunications satellites significantly actualize the challenge of improving large-sized foldable solar arrays (LF SA) reliability. The reliability of any equipment to be implemented onboard of a spacecraft depends mainly on the quality of their ground experimental test development (GTD). To ensure high quality GTD it is important to accept the correct concept of SA reliability validation, taking into account the specifics of the SA design and the real capabilities of the test facilities. The paper describes constituent parts of the concept allowing validating the large-sized foldable solar arrays reliability at the phase of ground experimental test development. There has been obtained the system of differential equations which describes SA deployment using the off-loading system and, as a result, solving of the differential equations system to estimate errors introduced to the SA elements motion dynamics by the test equipment is given. “Yamal-401” spacecraft SA mechanism reliability has been calculated. The stresses impacting SA mechanism elements during deployment under zero gravity, used during calculation and design of “Yamal-401” spacecraft SA have been defined. The developed methodologies of numerical tests have allowed validating the reliability of all large-scale SA structure elements, under all extreme cases, with regard to the available test facilities. This approach allows performing experimental test development of any large-size SA under development for new generation spacecrafts using existing experimental test facilities and equipment. The results of the research have been used by JSC “Information satellite systems named after academician M. F. Reshetnev” at the phase of ground experimental test of large foldable SA structures for “Express-AM5”, “Yamal-401” spacecrafts and other spacecraft types.

The importance of the problems of generation and energy storage on Board of space vehicles increases very quickly. In such a case, demands on spacecraft are constantly increasing: increasing information bandwidth and active lifetime, reducing development time and manufacturing, reducing the cost of satellites. Available publications on the subject are of a survey nature, or dedicated to individual issues such as, improving the efficiency of solar panels. The system of power generation is one of the most important on Board systems of the space vehicles. Design and characteristics of the system largely determine the appearance constructive, active lifetime in orbit, functionality, reliability, weight and size and economic performance. The mass of the onboard power supply system of domestic satellites is up to 25 % by weight, volume and cost of the space vehicle. The failure of the system entails failure of the space vehicle. This article presents a brief review of modern power supply systems of the space vehicles from a position of power and reliability. The factors affecting the availability of energy consumers on Board of the spacecraft are considered. Also the state of development of lithium-ion batteries which can improve their specific characteristics, as well as the increase of cycles of charge-discharge is examined. To increase the supply of space vehicles, the proposed device, including chemical and kinetic energy storage is offered. The combined storage together with the power supply system of the satellite allows maintaining the necessary supply of onboard equipment and compensating peak consumption on Board of the satellite. The principle of operation of this storage in the mode of accumulation of energy in the mode of bestowal it into the system to consumers is described. The kinetic energy of the rotating masses with brushless motor operating in generator mode and oscillators is converted into electrical energy.

In this article, the authors describe creation of software for spacecraft’s command and measuring system of onboard equipment test preparation and conduction. The command and measuring system performs data exchange between the Earth and onboard control complexes with the help of two data types: telecommands and telemetry. The software is designed to solve the task of the command transmission and their execution control in accordance with the telemetry frame values. It expands the possibilities of the control and measuring equipment’s software complex implemented in JSC “Information satellite system” named after academician M. F. Reshetnev”. The authors have the set of tasks and identified the main functions of test preparation and conduction that require software support. For this purpose, we have built a simulation model of the onboard equipment’s command and measuring system function during command reception and transmission. The model contains a set of subsystems’ software simulators demonstrating the logics of the command and measuring system’s work and the algorithms of data interaction between the onboard systems and the Earth control complex. The authors have described realization of the software functions identified on the basis of the simulation model: creation of the telemetry command and structure base, setting of the ways to display fields, creation of the list of commands, reference values and parameters of transmission, test conduction and analysis of command execution in accordance with the telemetry frames. Our software allows preparing and conducting tests. In order to prepare tests, the onboard equipment designer creates a command base in a graphic editor. On the basis of the command base, he creates different test procedures, choosing commands, tuning transmission, setting commutation interfaces, command respond waiting time, number of repetitions, ways of transmission, the controlled fields and telemetry values. The software performs the formulated test procedures both in auto and manual mode. While conducting tests, the software controls the telemetry parameters by the set limit conditions and demonstrates the results of the analysis. For the purpose of test visualization, the authors have designed a command reception and transmission monitoring window. The window displays the list of commands, time of their transmission and execution response, as well as the reference values of the set telemetry parameters. The data are constantly updated in accordance with the current condition of tests and the incoming telemetry packages. The designed software subsystems provide clarity of building complex sequences of test procedures of command reception and transmission, as well as simplicity and correctness of the results display.

The paper presents the experimental results of determination of the electric fields characteristics around ESD source on dielectric materials of spacecraft. For that purpose, the authors consider different types of ESD impact factors to board the equipment such as electromagnetic interference, capacitive interference and current injection to the equipment body. Each impact factor has its own physical bases caused by the interactions between the dielectric material of spacecraft and plasma of magnetosphere. To provide necessary impact conditions the authors applied the special generator with gas discharge device as ESD source. This device can be modified by different types of antennas which correspond to all ESD impact factors considered in this work. The generator also provides necessary characteristics of primary discharge such as time front, amplitude and frequency of current pulses. Using special workplace which includes positioning device for making measurements of electric field intensity in spherical coordinate system the authors obtained extensive statistics about electric field fluctuations caused by ESD. From the results it follows that the most significant electric field fluctuations corresponds to discharge current injection. Obtained electric field characteristics from ESD could be very helpful in security for radiated electromagnetic compatibility of spacecraft because its influence can lead to anomalies in spacecraft equipment functioning. The results of investigation could be applied in electromagnetic compatibility.

Now in the aerospace technology there are three main constructive and technological concepts - supported, sandwich and lattice. Basic feature of the first two concepts is that load is generally perceived by a covering, and edges or filler provide flexural rigidity and resilience to stability loss. In lattice constructions the basic bearing elements are ribs which provide at the same time membrane and flexural rigidity of construction and are made of the unidirectional carbon fiber composite material having high specific rigidity and durability. Composite lattice cylindrical shells are widely applied as load-bearing units of spacecrafts. In use as a part of the spacecraft such shells are exposed to complex influences of static and dynamic loadings. Influence of these loadings leads to emergence of tension differing in different parts of a shell in ribs of lattice structure. The construction considered in this article has additional longitudinal ribs in the areas of coverage of axial loadings. Depending on value of these loadings it is possible to regulate distribution of longitudinal ribs on perimeter, and also their quantity and length. Efficiency of entering into lattice structure of a shell of longitudinal ribs is shown in this article. The task of determination of the first frequency of longitudinal and cross oscillations of a lattice cylindrical shell with spiral and ring ribs and also of a shell with variable rigidness is solved. The analysis of influence of number of pairs of spiral ribs and their angle of unwinding on value of the first oscillation frequency is made. For a shell with variable rigidness influence of these parameters on its level of deforming from action of the lateral bending force is shown, and also assessment of cross stability is made.

The object of the study was the soil and the soil in the storage area of KRT military unit 12313 (technical missile base), which was located in 11 km south-west of Pamyati 13 Bortsov village Emelyanovsky district of Krasnoyarsk region. The levels of radiation (exposure and equivalent doses of external gamma-radiation levels of alpha- and beta-fields, the specific activity of radionuclides, including man-made cesium-137) on the object correspond to background characteristics. The concentration of KRT in soil is 0.001 mg/l, which corresponds to the level of “Danger” according to the testimony of the army device of chemical investigation. Bioindication with the use of Pinus sylvestris L., as well as the bioassay using Lepidium sativum L. showed that after the elimination of the military unit near the settlement of Pamyati 13 Bortsov due to contact with soil significant amount of KRT was unfavorable ecological situation that has reflected in maintaining a high level of phytotoxicity of soil. Special structures, debris, remains of tanks, fuel valves with chemical contaminants are ownerless there. This requires conducting the reclamation of the area. When carrying out detoxification and rehabilitation of soils a strong spatial irregularity of the level of residual contamination must be considered. To calculate the volume and technology of works it is recommended to carry out microbiological analysis of soil and to make a detailed map of phytotoxicity. When drawing the map of phytotoxicity it is recommended to consider the following set of indicators: the energy of the germination test cultures, mitotic index, and length of seedlings on the 5th day of cultivation.

The article presents the study on the driveline experimental design, basic formulas, defining function selected: the torque of the drive motor, the experimental factors: braking torque braking device, engine speed, driveline length, bend angle driveline. A brief description of the equipment, which is a stand, comprising a motor technology transmission driveline, the loading apparatus which are connected in series, and the loading device is hydraulic, comprising: a hydraulic pump, a choke, a filter, a pressure gauge, safety valve, tank, heat exchanger. The design of the proposed stand allows you to explore the driveline of different sizes at different angles of knee driveline. The stand is characterized by simplicity of design, a large range of parameters of loading and ease of setup thanks to the movable frame and vernier, calibrated in units of angle fracture driveline. The stand has a number of advantages: the test driveline while avoiding overheating of the braking system by cooling the working fluid, the improvement of operating conditions by providing a smooth regulation of the braking torque. To control the set parameters testing regimes instrumentation: strain gauges as gauges torque and braking moments, as a recording device using a dual-channel oscilloscope was used. The strain gauges were calibrated in torque and braking moments units empirically using technological devices. The task of the experiment is to find the optimal conditions driveline operation, namely the determination of the maximum efficiency of the driveline depending on the selected length and angle fracture driveline. The above method of design of experiments is designed for experimental studies of various drivelines with various types of bearings. Getting a polynomial regression model, the objective function - torque on the selected constructive-regime parametres of driveline allow further use of search methods the minimum values of the objective function, and, consequently, the efficiency of the transmission and corresponding to these values of constructive-regime parameters, allowing in the future to design phase of such programs to assign them reasonably, thus reducing design time frame while improving the quality of the design decisions, and to use significantly save energy while improving the transmission resource.

The research of shock interaction is of paramount importance for solving problems of theoretical orientation (study of the internal processes impact processes, the study of physical and mechanical properties of materials under dynamic loading) and practical, applied orientation (improving the reliability and efficiency of machine parts, the use of shock interaction in various processes of surface plastic deformation, hardening, marking, etc.). These studies are relevant and always in demand in mechanical engineering, especially in aircraft, rocket building, engine building, automotive industry, etc. The work is devoted to the study of shock interaction, using the research of stand drums on the basis of the linear electrodynamic actuator. The aim of this work is to assess the possibility of using linear actuators, because of their design features and modes of operation, the study of different shock processes. The comparative analysis of various impact devices (hydraulic, pneumatic, electric) discusses the advantages and features of the linear electrodynamic actuator, the mathematical model of the dynamics of the actuator in the shock regime. The results of mathematical modeling of the dynamics of working for different sizes of the linear electrodynamic actuator showed good agreement with the data of actual samples. The variant of use of research stand as a calibrator shock and vibration - electrodynamic calibrator is shown, its scheme is given, especially the calculation of the calibration method of the strike, the main technological and structural parameters and the results of experiments for calibration of the vibration sensor, which allows, after appropriate modernization, and configuration, use of electrodynamic calibrator in Metrology are shown

In the manufacture of aircraft parts electrochemical and chemical processes with high temperature working liquids are used. Now the use of hot water, steam, electric heaters for heating fluids are not effective. The article presents the experimental setup for hot water and aqueous solutions of AC power frequency. The article describes the method for testing and given expression for calculation of specific electricity consumed and the resulting specific heat density. At low power density ratio of the thermal energy released in the fluid by passing an electric current through it to the amount of electrical energy supplied to the heating fluid is close to unity. The second feature of this process is independent nature of the change ratio of the thermal energy released in the fluid by passing an electric current through it to the amount of electrical energy supplied to the heating fluid, depending on the specific power on the type and concentration of salts in the water. It was found that on heating water and aqueous solutions depends on material electrodes. Thus, the use of the titanium electrode gives higher values of the ratio obtained to the thermal energy consumed electric. It is shown that the contribution of the magnetic field in the heating fluid, located between the electrodes, negligible. The process of heating the water and water solutions is carried out based on independent from each other mechanisms: the electrochemical reactions on the electrodes; heat generation in the electric double layer; by eddy phenomena in the volume of water.

Important aspects of innovative activity are considered. The relevance of work is in a demand of innovations and innovative process in machine-building branch. In introduction the main tendencies of development of world economy and a choice of a vector of development of the Russian economy, namely an exit to a trajectory of the advancing development of national economy are designated. Characteristics are given to the main participants of innovative activity to the innovator, the innovator and the investor. It is established that subjects of innovative activity are the enterprises, the organizations, and the individuals who are directly participating in development of innovations and creation of prototypes of new production, and also those who renders financial, information, marketing, patent and license, leasing, marketing and other types of service. It is especially noted that for realization of the knowledge-intensive and difficult innovations in such branches as the space-rocket industry merger of the enterprise organizations is formed: consortia, concerns, holdings, financial and industrial groups, etc. Using a scale effect and having the big capital, large corporate business is capable to master the strategic technologies having priority value for achievement of national economy of scientific and technical progress. Among organizational structures of innovative process the special role belongs to small enterprises. Efficiency of their activity is defined by quality of the innovative environment. Due to the need of development of innovative infrastructure business incubators are considered as the main tool for development and support of the small innovative enterprises. In the conclusion need of development of communications between participants of innovative process, and also a key role of innovative infrastructure for functioning of the economy based on knowledge is emphasized.

To ensure competitiveness of enterprises of the Russian Federation in domestic and international markets in the current economic conditions it is necessary to implement strategies aimed at high-tech and innovative development. In this regard, the enterprise producing products for several industries, such as oil and military-industrial complex, need to meet simultaneously the various regulatory requirements imposed on its management system. In this context, the aim of this study is to examine the requirements of international and national standards, as well as defining the approach to their implementation on high-tech enterprises. The regulatory support of enterprise management systems is studied in the article and the trend to change it is reflected. The particular attention is paid to the international standard ISO 9001:2015 which specifies requirements for a quality management system and which may be one of the most important tools in the development of innovative high-tech enterprises. The new version of the standard adopted in 2015, contains significant changes to the requirements for the management system of organizations, in connection with this it is relevant to consider them. Therefore, the authors analyzed the changes and represented the differences from the standard ISO 9001 version 2008. It is also noted that the international standard ISO 9001:2015 is focused on the use of modern approaches in management. Due to the fact that the concerned parties increasingly make demands to the high-tech enterprises to confirm the conformity of their management systems to international and / or industry regulations, the authors determined the mechanism of their implementation. The authors analyzed the requirements of the standards ISO 9001:2015 (GOST R ISO 9001-2015), GOST RV 0015-002-2012 and specification API Q1 (9th version). The analysis revealed easily integrated areas, as well as specific areas requiring further development and implementation to the activities of the high-tech enterprises. The results of the research will allow enterprises to align the management system that focuses on quality assurance.