Vol 17, No 3 (2016)

Improving the reliability of mirror antennas increasing in size when more and more strict requirements to the deviation of the sizes of a paraboloid, and the miniaturization of electronic modules and a seal mounting on circuit boards, are pressing challenges, the solution of which is associated with high precision measurements at ground-based experimental testing chamber, where the test object. The reliability is directly related to durability, which, in turn, depends on flowing in designs thermo-strength processes in the conditions of orbital flight. The theoretical results are confirmed by calculations in the process of ground testing. The main parameters determined during the experimental research are the relative deformation of the umbrella antenna or circuit boards at various points. For PCBs proposed to apply two mutually perpendicular stripes along and across the tabs on the sides and in thermal vacuum conditions to conduct precise measurement of displacement labels at different temperatures. Then at multiple magnifications on the microscope it is necessary to investigate the size of the microcracks, which can take for allowed deflection. Precision of measurements should be at most 1/3 size of the crack. The proposed method is an improvement of known methods of applying brittle coatings testcustomermap. You can also use methods based on the use of sensitive optical coatings and methods of holographic interferometry, which, however, usually not possible to measure the linear movement with the required accuracy, especially when a large number of controlled points. Using the results of work performed in practice, the design of mirror antennas and on-Board electronics for space applications will increase its reliability by reducing design trial and error, optimization of the operation modes in operation.

The definition of the Cayley graph was given to the famous English mathematician Arthur Cayley in the XIX century to represent algebraic group defined by a fixed set of generating elements. At present, Cayley graphs are widely used both in mathematics and in applications. In particular, these graphs are used to represent computer networks, including the modeling of topologies of multiprocessor computer systems (MСS) - supercomputers. Since this direction is actively developed. This is due to the fact that Cayley graphs have many attractive properties such as regularity, vertex transitive, small diameter and degree at a sufficiently large number of vertices in the graph. For example, such a basic network topology as the “ring”, “hypercube” and “torus” are the Cayley graphs. One of the commonly used topologies MCS is a k-dimensional hypercube. This graph is given by k-generated Burnside groups of period 2, which is denoted B ( k,2 ) . The group B ( k,2 ) has a simple structure and is equal to the direct product of k copies of the cyclic group of order 2. A generalization of the hypercube is a n-dimensional torus, which is generated by the direct product of n copies of the cyclic groups whose orders may be different. In this work, We researched the structure of the Cayley graphs of group B ( k,4 ) - Burnside k-generated groups of period 4 (and some their quotients). Then we compared these graphs with the corresponding toruses and hypercubes. The analysis is shown that the graphs B ( k,4 ) have better properties in comparison with hypercubes and toruses. Therefore, they deserve attention in the design of advanced topologies of MCS.

Calculating the three-dimensional elastic composite cylindrical shells with different coefficients of fullness that is reduced to the construction of discrete models consisting of complex curvilinear multi-grid finite elements has been proposed. The basis of such elements construction is curvilinear double-grid finite elements. Double-grid and complex multi-grid elements are designed based on the basic finite element models of composite shells which take into account their heterogeneous structure and have high dimension. Constructing the curvilinear double-grid and complex multi-grid elements in the local Cartesian reference systems has been shown. Displacement fields are interpolated by known degree polynomials of various orders, the stress state is described by the three-dimensional elasticity problem (without introduction of the simplifying hypotheses on the nature of the displacement fields, strain and stress distribution). Approximating polynomials and the equations of three-dimensional elasticity problem are recorded in the local Cartesian reference systems. Advantages of the proposed elements are that they describe the three-dimensional stress state in composite shells, take into account their heterogeneous structures, complex fixing and generate multi-grid discrete models with a small number of nodal unknowns. The dimensions of multi-grid discrete shell models are by several orders less than the dimensions of the basic ones. Time spending of the finite element method (FEM) realization on a computer for discrete models of multi-grid composite shells is significantly less than for the basic models. A complex multi-grid element of the 3rd order to calculate the composite cylindrical shells is proposed. The FEM calculation example of cantilever sandwich shell using complex multi-grid elements of the 3rd order has been given. Shell calculation results show the high efficiency of the proposed complex elements.

The article is devoted to the structural modeling of resource management of heterogeneous distribution systems of information processing based on multi-agent approach of the design of distributed information systems. In the introduction of the article the urgency of the problem for the decision-making process is proved. We describe the main difficulties encountered when we make informed and timely decisions at forecasting and disaster management on the scale of the Russian Federation. Further objective of the study is formed, and the tasks required to achieve it are described. Starting with a description of the distinguishing features of the unified state system of prevention and liquidation of emergency situations of the Russian Emergencies Ministry, the authors come to the conclusion that the system fits the generally accepted concept of heterogeneous distributed information processing system. Below, the construction of multi-agent approach to resource management of heterogeneous distributed information processing system as the least costly financially, and meets the necessary criteria is justified. In the body of the article a complete description of levels built models such as the - level of intelligent agents, the level of computer equipment agents, route management level is given. The structure of the system is described. The article details the typical functionality of the following: a software component management agent compute node load monitoring agent and monitoring agent communication channels, data transfer agent, load balancing agent, agent utilization of communication channels forecasting reactive agent of the primary data sources. At the end of the work the possibilities of further development of the model, as well as the conclusion about the necessity of its algorithmization for practical testing and implementation in practice are considered.

The research examines the technique of synthesis of the PID controller control systems for objects of the second order, characteristic of mobile, construction and road-building and road-building machines. As the theoretical basis the modal method is considered for linear systems with respect to the location of the actual poles. The results of analytical research that establishes the influence of the poles on the range of variation of the transient response are given. The analytical expressions defining the values of the components of the transient characteristics of the closed-loop automatic control system with object of the second order have been taken. Expression for calculating the coefficients of the PID regulator, including coefficients of the transfer functions of second order with given value of the actual poles have been defined. The techniques on a concrete example in the environment of Mathcad have been checked. Using the proposed method characteristic features of the influence of model input factors impact on the transition process have been revealed. Simulation showed that at a certain value of the coefficient of the first derivative in the numerator of the transfer function is not zero; the initial value of the transient response will be included in the 5 % zone steady-state value. This suggests the possibility of a significant reduction of the transient time.

Embedding of digital watermarking (DWM) is a technology of hiding messages in the digital signal (for example image, audio, video). It provides transferring of important information in the workflow system in production. Any digital signal may be used by the way of hiding information. The type of the signal affects the process of conversion only. This technology is applicable for system of workflow including aerospace industry. Through digital watermarks the important message can be transmitted, system information can be hidden in documents. DWM can help to protect contents of document including images and snapshots. In the paper as content static images were used, as transmitted information text messages were used. The digital image may be considered as a set of pixels with various brightness and colorfulness, so we can operate with it. Also we use frequency image’s domain, where we can manipulate with frequency coefficients to hide user’s information. Both approaches are widely used in marking technology. In the work process spatial method Least Significant Bit and frequency method of Koch-Zhao were used. These methods were compared by using quality assessments for resulting images which contains a digital mark. Numerical results were obtained by using known metrics: structure similarity and peak-signal to noise ratio. Experiments show the advantages of spatial methods against frequency algorithms in the cases when filled image was not exposed by distortion before a moment of extraction information message. In all other cases frequency methods are appropriated.

For over thirty years composite lattice cylindrical shells with high specific strength and stiffness are used in rocket and space technology. Lately composite lattice cylindrical shells are widely used as casings of spacecrafts. Lattice shell is the supporting structure to which devices and spacecraft mechanisms are attached. One edge of this shell is attached to the launch vehicle through the adapter. Today lattice cylindrical shells which used as casings of spacecrafts do not have cutouts and holes in their structure. This fact is significantly complicates the installation of equipment, docking of connector cables and pipes located inside the lattice cylinder.Obviously, the presence of openings in the shell facilitates the installation of equipment,but at the same time affects the stiffness characteristics of shell. This article describes an algorithm for creating a finite-element model of lattice cylindrical shell with openings made by composite material. The problem of determining the first frequency of the longitudinal and transverse vibrations for shell, one end of which is rigidly fixed and on the other end is attached an absolutely hard disk, is solved. It is analyzed the influence of the hole size and stiffness of bordering rib on the magnitude of the first frequency. Values of the first frequency of the longitudinal and transverse vibrations for lattice shell with openings of different sizes are shown.Graphs of the first frequency of the longitudinal and transverse vibrations depending on the width of the bordering rib are presented. The value of the first frequency of the longitudinal or transverse vibrations of shell is a characteristic of rigidity of the structure.Therefore, modal analysis results allow us to draw some conclusions about the impact of openings on the stiffness parameters of the lattice shell.Obviously, the openings decrease the first frequency of the longitudinal and transverse vibrations of shell. Bordering rib improves the rigidity of shell with openings.With increasing the width of the rib there is an increase the respective first frequency oscillations.Influence of the width of bordering rib the more noticeable than the larger size has an opening in the lattice structure.The obtained results can be used in designing of power constructions in spacecrafts.

In this article there is the assessment of possibility and effectiveness of accelerated unwinding of the rotor booster pump of liquid rocket engine under start-up conditions. A method for reducing the error of rate in the unwinding of the booster pump and turbopump units is based on the organization in the process of starting the engine with supplying additional working liquid to the turbine of boost directly from the output of the pump of the oxidizer. There is a rocket engine, working on the components of the liquid oxygen - kerosene, made according to the scheme of oxidizer generator gas with afterburning. During rocket engine start-up and turbopump rotor unwinding, the maximum pressure in the engine is realized at the outlet of the pumps. When starting the engine using additional liquid driving, which starts earlier than the gas driving, the boost pump acceleration occurs much earlier. To analyze this problem, a dynamic mathematical model of the rocket engine is using. The goal of the calculation is to study start-up process of rocket engine to select the static parameters of liquid driving line, providing engine start under the lowest possible components on the pressure in the engine inlet. Among the parameters, that affect the operation of the liquid driving, the inertial pressure losses selected in the line supplying the additional working liquid to the turbine of boost pump. Mathematical modeling of engine start-up in the absence of liquid driving, and at present, but with different characteristics of the driving line was conducted. The efficiency of the use of preliminary unwind of oxidizer boost pump by additional liquid component, coming directly from the output of the pump the oxidizer is shown. The influence of the value of the area of the nozzle section of the liquid driving and inertial losses of pressure of additional oxidizer line on the effectiveness of unwinding of the rotor booster pump of liquid rocket engine when engine start was conducted.

One of the main issues in the design of low-sized reaction flywheel was the selection of bearings, because there are strict limits on the size and weight of the device that allows using only ultra-light series of ball bearings. At the preliminary stage of design calculations verification of safety factors for loads in mechanical tests and of flexural strength of axis for mechanical testing identifying by critical sections was carried out. Rotor system of low-sized reaction flywheel consists of a flywheel mounted on the outer rings of ball bearings, inductors, and the rotor’s magnet of the rotor position sensor. The most dangerous moment is the unbalance of the rotor system as there is a direct link between the dynamic loads and the level of contact pressure between the bearing balls and raceways. Upon reaching significant values of these stresses flaking on the tracks and rolling elements is possible. Furthermore, the pressure unbalance inevitably causes the flywheel shaft of the friction force and hence heat, which leads to an increase in drag torque of the rotor, and also accelerates the aging process lubricant. In accordance with the general requirements imposed on the rotor system of low-sized reaction flywheel it was subjected to dynamic balancing, because only this type of balancing ensures the elimination of all types of unbalances with the required accuracy. To carry out this process step the rotor system has two correction planes located on the rim of the flywheel in the areas of maximum distance from the axis of rotation. Balancing is carried out by removing material in the areas of the annular grooves of the correction planes. Comparing the characteristics of low-sized reaction flywheel and foreign analogues shows that the parameters correspond to foreign models.

In the article authors examined problems of electrical tests of spacecraft electrical systems (SES) with special simulation systems to reproduce electrical characteristics of spacecraft power system (PSS ECSS). The relevance of these systems and disadvantages of known simulators are discussed. A new automated system, which can be used to carry out SPS electrical tests in work and emergency modes, study noise immunity of spacecraft electrical systems with given noise magnitude, frequency and shape is considered. ECSS provides stable 27 and 100 V power to SES and contains two special power supplies (ISEP) providing main functions and control computer. In the article the authors show that combining regulated power supply and noise signal generator in ISEP leads to significant topology simplification, improvement of operation characteristics and better reproduction of spacecraft power system impedance frequency characteristics. In the article topology of PSS simulator with output voltage range up to 100 V (ISEP-100), containing constant voltage supply, output voltage regulator, multifunctional low-latency protection device (LLPD) and digital control and measurement system, is examined. Output voltage regulator based on dual power regulation topology, which can provide required static and dynamical properties and satisfactory specific power. Continuous voltage regulator (CVR) provides energy quality, reproduce required impedance frequency characteristics of onboard SPP, allows to induce test signals of required shape on power bus in frequency range up to 1 MHz; Switching regulator limits power dissipation of CVR by voltage regulation on CVR transistor current regulator. Developed and studied LLPD, which is able to shut down SES on overvoltage and overcurrent conditions above specified levels and provides AC network phase loss detection. LLPD delay can be defined in range 2 to 1500 us. Developed PSS ECSS allows carrying out entire program of spacecraft electrical systems tests and operated in Academician M. F. Reshetnev Information Satellite Systems, Zheleznogorsk, where it was used for onboard repeaters tests of various spacecrafts.

A large-size antenna’s reflector working at geostationary earth orbit has an approximate diameter of 48 meters while requires development of a special extension mechanism for its telescopic tubular spoke deployment. The most important requirements are the following: weight less than seven kilograms, power consumption ( ), movement along the longitudinal axis of the spokes at a distance of more than eight meters and an axial force of at least 2000 N. The results on the development and creation of a new mechanism for link spokes telescopic extension for large-size transforming reflector are presented. The descriptions of extension mechanism as well as the principle of its operation and testing results under industrial conditions at JSC “ISS” are given. The working principle of the special extension mechanism is based on the movement of two disks along curved trajectory inside the tubular surface of stationary part of the spoke. Mechanical catching of moving parts is based matching the pins installed on disks against junctions located on the stationary part on the spoke. TDI SIE SB RAS had developed and produced the mechanism for the link spokes telescopic extension of reflector with 48 m in diameter. Such mechanism has been successfully tested at JSC “ISS”. Technical characteristics and the tests results of the mechanism for the link spokes telescopic extension of reflector and shafts in the composition of spokes demonstrate that the developed mechanism fully meets all requirements. The developed original mechanism for telescopic extension of reflector’ link spokes and shafts is highly reliable, has a good mass-dimensional characteristics (mechanism mass is less than 7 kg). Extension mechanism implements significant efforts (the efforts of 200 kgf) in the axial direction without significant effort in the radial direction and it allows for repeatedly reversing the movement of the links without adjustments and settings. Only single electric motor is used in the design of extension mechanism at all stages of spokes disclosure. The created extension mechanism can be applied to any telescopic systems. It can be used as a means for various devices displacement in long (virtually unlimited length) pipelines.

Solar thermal propulsion (STP) with high-temperature concentrator-absorber system (CAS), as a power source, is observed. Ordinary observed STP with simple single-stage isothermal absorber-heat exchanger, executed as an absolute black body, requires high accuracy of reflecting surface of solar mirror-image concentrator and high-precision tracking conditions to the Sun on active legs of multi-burn injection trajectory. Reduction of these requirements is possible at use of CAS with organization of non-uniform heating of hydrogen in absorber which temperature corresponds to exponential law of distribution of radiant flux density in focal sunlight spot. Energetic efficiency of such CAS is higher in comparison with the isothermal one. Single-stage, double-stage and extreme-not isothermal (multi-stage) CAS are considered. Results of simulation of STP with the considered CAS for upper stage application in mission of non-coplanar payload transfer from LEO to GEO are shown. It is shown that ballistic efficiency of solar upper stage with the considered STP can more than twice exceeds capabilities of modern liquid-propellant upper stages. Comparison of ballistic efficiency of STP use with different CAS as means of inter-orbital transportation is carried out. It is shown that the efficiency rises with increase of ratio of non-uniformity of hydrogen heating in sunlight absorber-heat exchanger and can be 30 % higher as compared to ordinary STP use. Such relevant CAS parameters as accuracy parameter of mirror-image concentrator and hydrogen heating temperature in the absorber-heat exchanger are considered. Optimal relevant parameters for criterion of maximum of payload mass for the considered CAS types are determined, and recommendations for their choice with technological restrictions are suggested. Dimensional parameters of concentrators for the cases of isothermal and staged absorbers are shown. Conditions of orientation to the Sun for the different CAS are observed. It is shown that requirements to the Sun tracking system in dynamic orientation mode can be quite provided by modern hardware components, especially in the case of non-uniform heating of hydrogen.

Currently, systems of orientation and stabilization of spacecraft are widely used in Electromechanical Executive bodies (EMIO). Electromechanical Executive body has a high accuracy of orientation and does not require the working fluid for its operation. This article describes the modern Electromechanical Executive bodies of systems of orientation of space vehicles of domestic and foreign production and gives their main characteristics. The review revealed that Electromechanical Executive bodies, both domestic and foreign production is made roughly the same pattern, namely, on the basis of the reaction wheels on roller bearings and their technical and resource characteristics are comparable. Nowadays in the space industry there are two distinct trends: the trend of increase in weight and size characteristics of the spacecraft caused by the increase of the target hardware, and the trend of growth of the active lifetime of the spacecraft. The increase in weight and size characteristics of the spacecraft (SC) leads to the fact that there is a need to increase the control torque of the Electromechanical Executive body. Managing time can be increased by increasing the mass or dimensions of the Electromechanical Executive body or by increasing the speed of rotation of the motor flywheel, included in its composition. Based on the specifics of space technology, namely because of the restrictions on its weight and size characteristics, the most appropriate way of raising the control point of emio is to increase the rotation speed of the motor flywheel. Active lifetime (SAS) of the spacecraft can be increased by increasing the period of operation of components and assemblies of the spacecraft, and including Electromechanical Executive body and due to redundancy of the most critical nodes SC. Preferred is the improvement of SAS by increasing the active lifetime of the components of SC. The article gives a brief analysis of the possible causes of failure of existing Electromechanical Executive bodies in the operation by increasing the speed of rotation of the motor flywheel and identifies the most likely cause of failure is the destruction of the ball bearing supports Electromechanical Executive body due to the overload acting on it. The questions of reliability and durability of ball-bearing supports, the problem of determining these characteristics for the bearing have been considered. The possible method of modification of a given support has been studied. The major factors limiting the use of ball bearings in Electromechanical Executive bodies have been determined. Classification of existing supports Electromechanical Executive bodies and means of contactless suspension of the bodies used in modern technology has been given. Comparative analysis of gas and magnetic bearings has been conducted. The advantages and disadvantages of gas bearings have been studied. Magnetic props of various types, their comparative analysis, identified the feasibility of their application with satisfactory dimensional characteristics have been considered. The task to create a passive magnetic support on the basis of highly coercive permanent magnets has been set.

Relevance of the work is determined by the increased competition in the global market development of satellites, which requires the reduction of costs for the development and spacecraft launching. The obvious way to cut costs is to reduce the launching mass of the spacecraft, that allows us to apply to spacecraft launching into geostationary orbit cheaper launch vehicles of the middle class, or to launch several space vehicles with one launch vehicle. An alternative solution to this problem is the combined method of spacecraft removing. Combined method of spacecraft removing has the advantage of insertion time regarding the method of removing using only the electric propulsion thrusters, regarding the method of removing by chemical two-component propulsion thrusters - the amount of fuel. Consequently, the combined method of removing will allow the spacecraft to move quickly through the area of the inner radiation belt of the Earth using the two-component chemical thrusters and electric propulsion thrusters for further removing spacecraft on operational orbit. The aim of research is to assess the effectiveness of removing the spacecraft on geostationary orbit by the combined method, the optimization of the mass of fuel for removing. As the results of the performed work the following things can be considered: optimization criteria of the combined method, the method of optimization of the fuel mass and the corresponding set of programs in MatLab. Also, the following calculations and analysis of the results were carried out: launch spacecraft of various launching mass by combined method, using launch vehicle “Proton-M” with the upper stage “Breeze-M”, the Baikonur сosmodrome, Kazakhstan, and with the help of the launch vehicle “Falcon-9v1.1” cape Canaveral, the USA. In conclusion, according to the article launching with the help of launch vehicle “Proton-M” with the upper stage “Breeze” has a number of advantages than foreign launch vehicle.

The study focuses on carbon nanotubes (CNT) surface modification with transition metal atoms. CNT modification expands their scope and makes them more perspective in the production of micro- and nanoelectronic devices, which, in turn, can find application in electronic control units of space technology. We have considered the possibility of scandium and titanium atoms coating on the CNT surface. Selection of atoms is due to the potential possibility of creating uniform coating by these atoms that is impotent for practice application. The adsorbing capacity and the mobility of atoms play an important role during coating formation. Until now it has not revealed whether the non-uniformity obtained in the experiment is fundamental property or it depends on coating process technology. Understanding the basics of coating formation will help control this process. It is possible that the uniform coating can be formed only on tubes with certain chirality or diameter. In this research we propose and study the influence of radius, chirality and conductive properties of nanotubes on its interaction with scandium and titanium atoms. The theoretical study of single scandium and titanium atoms interaction with a set of carbon nanotubes ”zigzag” and “armchair” types has represented. The radius dependence of binding energies (Есв) and activation energies (Еа) for surface diffusion transition metal atoms in two nonequivalent directions are built. The influence of radius, chirality and conductive properties of nanotubes on Есв and Еа values are evaluated. The results show more strong interaction between the surface of the carbon skeleton and titanium atoms as compared with scandium atoms. The curvature of the carbon skeleton also facilitates more strong interaction between studied atoms and the surface of the nanotubes. It has revealed that the degree of influence on binding energy and diffusion barrier values decreases in the set: chirality - conductive properties - radius. In general, values of activation energies are low, that reports on possibility of atoms moving. Such possibility will facilitate the formation of the uniform coating. The data presented have been obtained density functional theory approach and the Vienna Ab initio simulation package (VASP). Nudged elastic band method has been used for finding transition states and potential transition barriers of metal atoms moving on CNT surfaces.

The aim of the article is to identify the factors that determine the attractiveness of an industry with a view to their further use in conducting strategic analysis. The information about the share of Russian companies in the total world production of rocket and space technology is given. A comparison of the level of competition on the Russian and world markets of aerospace industry in 2012-2014 is given. The characteristic of dynamics and trends of the world market of space activities is submitted. The structure of the world market of space activities, including the share of the private and public sectors, and trends in their changes is presented. The necessity of output of Russian enterprises of aerospace industry in the global market is justified. The article proposes an ordered list of the factors that determine the attractiveness of industries and markets products of rocket and space industry, which must be taken into account in strategic planning activities in the global market. The list of information sources and baseline data for the analysis of industries and markets is given. The comparative characteristic of the analytical and research reports on the state of and outlook for production of rocket and space industry, as well as on the possible direction of the market the first 20-30 years of the XXI century are submitted. The method for using the results of the analysis of the attractiveness of the sector for strategic planning of enterprises of rocket-space industry of Russia in the world market is presented.

N the article the author analyzes the factors of growth in defence industry. The analysis is based on the general regularities of the reproduction of capital. The approaches to the reasons of the role of different factors in increase of labor productivity on the example of classical, marginal, neoclassical theories are considered. The author gives the characteristic of the modern situation in economy and in defence industry. Due to the imposition of sanctions against Russia from the developed countries, the implementation of the program of development of defensive branches meets certain difficulties. Therefore the necessity of search, first of all, of internal sources of financing of conversions in the defensive industry is justified. Based on the theory of reproduction, reserves of growth are associated with accumulation fund and some part of compensation fund. Therefore the formation of necessary investment resources and their effective use assumes a new quality of financial system in the country and a new model of relations between real and nominal sectors of economy. The state is obliged to be guided not on the demand economy, but on the supply-side economy. Therefore it must create a distinct industrial policy where the policy of import substitution will become a component. In innovative economy a major factor of growth is knowledge. Reproduction of knowledge is subject to transformation of a human factor into the human capital which moves apart from boundaries of production and influences productivity and efficiency of work. The financial sector of economy has to provide adequate conditions of transformation of knowledge into a decisive factor of economic development and change the functional purpose.

Innovative activity is highly relevant means of adaptation of the military-industrial complex in accordance with the requirements of the time. Innovative activity of enterprises of the military-industrial complex in modern conditions is the most expensive to build the most advanced models of equipment on the existing level of knowledge, but it has far-reaching prospects both in equipment and in product sales. Organization of high-tech, competitive production is possible only on condition of military-industrial complex skilled workers that have high intellectual and creative potential. This increases the demands on management mechanisms related to the formation and development of human capital. The article is devoted to research and identify the characteristics of the human capital in the development and implementation of innovations at the enterprises of the military-industrial complex. In order to describe the characteristics of the human capital adopted a typology of innovations on the scale caused by the effects. The results of the study showed that depending on the implementation of strategic and ongoing innovation are changing the characteristics of the human capital of the structural elements: physiological capital, professional and personal capital, intellectual capital. The difference between the workers involved in the development and implementation of strategic innovation is the focus on the formation and development of human capital, while the workers involved in the implementation of current innovations focused on maximum utilization and human capital formation. The results obtained allowed to determine the main directions of formation and development of human capital for innovative development of enterprises of the military-industrial complex.