In order to implement the concept of acceptable risk all airlines should have the Safety Management System (SMS) from 01.01.2009 - at the request of ICAO and from 01.01.2010 - at the request of the Federal Air Transport Agency. State requirements for SMS have not been formulated clearly. Leading airlines, in an effort to meet international standards, develop and implement SMS on their own. So the implemented SMS differ in control settings (level of safety), procedures and methodological support of the processes of safety management. The summary of the best experience in development, implementation and improvement of SMS in leading airlines, allows to create a standard SMS to the airline, where the basic procedures required by the standards are systematized. The standard SMS is formed on experience in design, implementation and development of corporate SMS in three leading Russian airlines, in which the author worked in 2006-2015, and can be the basis of an SMS of the airlines operating the planes and helicopters. Taken into account in a typical SMS requirements of international and national standards, research results, developed and implemented methodical maintenance of management procedures level of safety, contributed to the successful passage of IATA periodic audits on developing standards of operational safety IOSA by the airline members and achieve the best level of safety not only in Russia but also in the world.

The article deals with procedural guidelines for delayed damage aircraft safe flights. This methodological support is intended to form the aircraft type minimum equipment list (MEL).It is suggested to use airworthiness provision as the basic criterion for MEL determination. In order to develop methodological support of safe flights with delayed damage it is suggested to follow the well-known methods of statistical and constructive analyses and theory of estimation methods. Functional system reliability of delayed damage flights isanalyzed alongside with functional system failure types and consequences.Modeling reckons upon the opportunity to analyze the functional system failure-free operation for any predetermined specified operation time, including the time between overhauls. Functional system failure-free operation analyses and estima- tion by means of suggested model supposes step-by-step approach in solvation of the following problems: every component of the functional system reliability estimation; failure-free operation of the functional system in the whole.Thus it is possible to determine and forecast acceptable rates of failure probability for every analyzed component considering airworthiness requirements at the aircraft maintenance facility.The initial data for modeling is the functional systems and parts failure statistic database accumulated from a cer- tain maintenance facility operation experience.The suggested mathematical support for MEL formation allows to update manufacturer specified MEL for the air-craft maintenance facility.

The interrelation between aircraft airworthiness maintenance process (AAMP) and the process of project management methodology application is demonstrated.A project portfolio can be formed based on the strategic objectives. The projects with the highest priority are carried out, including those which strive to improve the efficiency of AAMP. The proposed approach allows to find the priorities of specific projects realization, which are included in the airline project portfolio.The project aimed to improve the efficiency of the AAMP of AN-124-100 of "Volga-Dnepr Airlines" is presented as an example. The statistical data analysis of failures of AN-124-100 fleet has demonstrated that wing components most frequently fail, especially spoiler sections, which are subjected to honeycomb skin mass exfoliation and need to be modified. One of the expected project results should be the К1000 reduction of the wing spoilers not less than for 40 % and, respectively, the plane in total - not less than for 4 %.The work is executed in full compliance with the standards of project management. The passport of the project is given, which contains all the necessary information about the project: its goals, outcomes, results, timelines, action plan, budget and participants. A special attention is paid to the risks of the project, their probability assessment and the actions for overcoming possible consequences. It is shown that the implementation of the project "Introduction of aircraft AN-124-100 spoilers technology modification" allows to improve a number of production and technical efficiency indicators, with material, financial and organizational resources optimization.

The aircraft maintenance is realized by a rapid sequence of maintenance organizational and technical states, its research and analysis are carried out by statistical methods. The maintenance process concludes aircraft technical states connected with the objective patterns of technical qualities changes of the aircraft as a maintenance object and organizational states which determine the subjective organization and planning process of aircraft using. The objective maintenance process is realized in Maintenance and Repair System which does not include maintenance organization and planning and is a set of related elements: aircraft, Maintenance and Repair measures, executors and documentation that sets rules of their interaction for maintaining of the aircraft reliability and readiness for flight. The aircraft organizational and technical states are considered, their characteristics and heuristic estimates of connection in knots and arcs of graphs and of aircraft organizational states during regular maintenance and at technical state failure are given. It is shown that in real conditions of aircraft maintenance, planned aircraft technical state control and maintenance control through it, is only defined by Maintenance and Repair conditions at a given Maintenance and Repair type and form structures, and correspondingly by setting principles of Maintenance and Repair work types to the execution, due to maintenance, by aircraft and all its units maintenance and reconstruction strategies. The realization of planned Maintenance and Repair process determines the one of the constant maintenance component. The proposed graphical models allow to reveal quantitative correlations between graph knots to improve maintenance processes by statistical research methods, what reduces manning, timetable and expenses for providing safe civil aviation aircraft maintenance.

The article deals with the estimation algorithm for functional system reliability influence on the aircraft technical maintenance. The research results which allow to estimate the functional system reliability influence on the aircraft technical maintenance process are provided. The aircraft maintenance process effectiveness implies the maintenance procedures including pre-flight preparation, the flight itself, technical maintenance and storage.The research was aimed at forecasting the aircraft technical maintenance process considering the functional system reliability, with special attention payed to failure-free operation. The term failure-free operation stands for the ability to execute a required function within a given time interval at given conditions.The objects of maintenance -aircraft functional systems and their components have a great degree of failure-free operation, which has been a design requirement and is supported at aircraft maintenance and operation. Failures and malfunctions are seldom events. This fact leads to a limited statistic maintenance surveillance database. Classical methods of statistical analyses do not provide the sufficient fiducial probability for functional system failure-free operation estimation. Thus these methods do not allow to estimate its influence on the aircraft technical maintenance process effectiveness.In order to solve this problem it is suggested to use the method of flow diagrams and random sample statistical method for failure-free operation estimation-statistical modeling (Monte-Carlo Method). Reliability flow diagram method allowed to determine the functional system failure-free operation random sample dependence on the technical maintenance frequency.The initial data were: the functional system flow diagram, the list of the main equipment, functional system equipment failure random sample data. The use of statistical modeling allowed to estimate the dependence of functional system reliability (failure-free operation) on the technical maintenance frequency for expanded statistical database (a number of functional system maintenance and operation procedures).

The key steps of aircraft essential parameters and events monitoring during its operation are considered in the article. Conditions for specific risk monitoring are also presented.The notion of fail-safe feature of aircraft functional systems is analysed, and the necessity of continuous process of safety flight level estimate is shown. The method of quantitative assessment of key events and risks probabilities with the use of modern software is proposed. This method contains 5 basic stages: The monitoring parameters setting - this stage is initial and begins with the consideration of organization safety culture, the main purposes and problems determination, the basic parameters and characteristics forming which are to be monitored. The event monitoring in operation - on this stage continuous process of key events searching and monitoring which are a thing of importance within the framework of the established problems takes place. This process is closely related to parameters monitoring set on the first stage. The event and risk estimate - this stage begins directly after the event has been discovered. The estimate process is as long as it is required to identify the event gravity. It also contains the preliminary risk estimate for using in prioritization of initial expanded estimate and in the working out of plan for activities realization. The working out of plan for activities - on this stage correction data is determined that will make changes to aerotechnics working out, operation, maintenance and to staff training directly in linkage to the problem event identified earlier. The activity carrying-out - the realization of actions according to the activity plan. This stage concludes prioritization, planning and problem carrying-out. The dependence set between the probability of failure situations and the degree of their danger is shown. The key factors which are subject to be estimated while aircraft operating and which aim with risk analysis to increase the safety flight level are justified.

Potentially new ways to improve civil aircraft fuel efficiency, based on the aircraft maintenance process optimization are considered. The data confirming the advisability of their further in-depth study and implementation in civil aviation airlines activity is given.It is shown that one of the reasons provoking the increase of fuel consumption at the cruising flight stage might be the necessity of the bypass of meteorological areas and of the flight altitude or airspeed change. These events are occasional. At the same time the most advantageous methods aimed at improving fuel efficiency are continuous aircraft climb or descent.One of these research directions is the implementation of continuous descent mode, rational routes of approach to the airfield, climb, choice of optimal flight modes in flights. This program is called “SESAR”. While its realization within the framework of the EC it is planned to reduce fuel consumption by 5 million tons a year due to its economy by 10 % after each flight. The similar program “NextGen” of air traffic optimization is accepted and is realized nowadays in the USA. The purpose of this program is annual improvement of fuel efficiency not less than by 2 % a year.Based on the conducted research the expanded list of recommendations for the realization of aircraft continuous descent system in flight, providing renunciation of horizontal flight areas at idling engines is presented.

The new calculated program complex which main task is to find the optimal algorithm of stochastic helicopter de- sign and assembling in terms of maintenance efficiency is described. It is shown that the use of the developed calculated program complex allows to efficiently solve the problems of helicopter construction with high-rating maintenance worka- bility factors.It is shown that for efficient problem solving connected with Maintenance and Repair costs reduction while heli- copter engineering and assembling in design office it is appropriate to use correlated analysis for maintenance workability estimation with the use of CAD system. The calculated program complex is based on mathematical apparatus of linear cor-related dependence of two-dimension (stochastic) process. The linear correlated dependence is considered as linear or anyconnection close to it between two variables for which the correlated analysis theorem is true.The algorithm of calculated program complex for helicopter maintenance workability estimation consists of five steps: choice of equipment that needs to be installed on the helicopter; correlation coefficient calculation for helicopters having this equipment and revealing of optimal variants of location; zone partition of the developed helicopter and analysis of possi- ble disposal of clusters in optimal order; disposal of clusters on the designed helicopter; correlation coefficient calculation, direct regression construction for the designed helicopter and comparison of these readings with helicopters-analogues. The calculation data of correlated analysis characteristics which indicate a possibility of increase of helicopter maintenance worka- bility level with a modicum of effort and time when working out the particular functional system is given.

On the basis of system approach the structure of the aviation activity areas on air transport related to monitoring and measurements of vibration parameters is presented.The technology analysis of laboratory tests of the onboard equipment control of vibration parameters is carried out. The issues related to ensuring the unity of measurements of vibration parameters are researched and summarized.While dealing with the works on metrological certification described in the article, the risks arising from aviation activity on air transport are taken into account. The certification methods of measuring channels of vibration parametersused on stands for testing GTE at the repairing of aircraft engines are developed. The methods are implemented when conducting initial and periodic certifications of test benches for twelve types of aircraft GTE in repair organizations. The reliability of the results of the conducted research due to the fact that they were carried out with the use of certified measurement equipment, included in the State register of measuring instruments. The research is conducted for a sufficiently high statistical confidence level with the boundaries 0.95. The studies have shown that running on air transport measurements of vibration parameters are metrologically secured, the unity of measurements and their traceability from the national primary reference to special measuring instruments, test equipment, and onboard controls of the aircraft is maintained.

The article deals with the problematic issues of planning the work of aviation units and offers one of the possible variants of their solutions by means of project management tools implementation in aviation units.As a key concept in the theory of planning, the author proposes introducing the concept of a project as a complex, non-repeating one-time action, limited in time, budget, resources and in clear guidance throughout the process, followingthe customer requirements. In aviation engineering service work, this also includes such works as operational preparationstypes, routine maintenance, aviation technology improvements, military repair etc.The use of network models can also easily specify the sequence of some of the actions (events), to make process flow charts and organizational charts.The main advantage of linear graphs is their clarity and simplicity. Linear graphs make it possible to optimize the work on a variety of criteria, including the equability of labor force, machinery, building materials, etc. At the same time,the main drawback of linear graphs is that they are difficult to correct in case of non-compliance with the deadlines or a change in their arrangement. These drawbacks are eliminated by a different form of scheduling - network charts.The scheme of planning the work of units using project management tools is given. To carry out the scheme theauthor proposes to use modern tools of project management, which allow to structure the process of maintenance activities through its decomposition into phases, tasks and subtasks, then to identify critical path tasks, construct the chart of implementation. The process model as a project allows to make the prognostic analysis and to improve the process according to it, for what a number of modern software packages that automate the functions of planning and planned types of work schedule control.

The consistency of the potential increase of fuel efficiency, based on aircraft maintenance optimization, is mathe- matically proved. The mathematical apparatus and a set mathematical model of aircraft spatial motion allow to analyze aircraft behavior on the stage before landing and to draw optimal flight path for minimum fuel consumption with fixed time.For effective problem solving the choice and realization of optimal flight paths are made. The algorithm for the problem of optimal civil aircraft flight control aimed at the most accurate realization of chosen soft path under limited time conditions is proposed. The optimization of the given process is made by solving a point-to-point boundary canonical sys- tem based on the Pontryagin maximum principle.The necessary initial data and conditions for the statement of problem are given. The mathematical model for the simplification of calculations is created and its equivalent representation is given by uniting problems of controls by thrust channels and the angle of attack as the thrust control function. The boundary-value problem is mathematically composed and the analytical apparatus of its solution is presented. Optimal aircraft landing paths reflecting the behavior of the angle of attack and thrust are constructed. The potential of this method is proved by the economic justifiability and its effectiveness, in particular the compar- ison of total aircraft fuel consumption on obtained optimal path to the classic path on which there are rectilinear sections what allowed to confirm the conclusion about the economical expedience and effectiveness of the method of aircraft con- stant landing while making flights.

The author dwells upon the problems of the technical condition of refueling complexes equipment continuous monitoring, which is an important factor in ensuring the safety and regularity of flights. The article deals with the results of the research into the composition and concentration of mechanical impurities from different layers of the regular filter EFB-15/120-104 0615 production number of NGOs "Unit", which has been removed from the supply line TC-1 aviation fuel tank farm from the State Reserve in the refueling tank farm "Vnukovo" and the filter control of Velcon company brand the CDF 230F, which is removed from the tanker, in order to assess their performance and service life prediction using X-ray fluorescence method.Illustrative and graphic research results are given, which allow to assess the effectiveness of the used filters. The assessment measuring of the found elements concentrations in different areas of the test sample: 4sm2 area, 1 cm2 and 0.25 cm2, cut from a cardboard filter area is made. The author determined that the average total Fe concentration on the filter was 8.3 g / m providing the fact that due to the operator information the filter pumped 2,020 m3 or 1,582 tons of fuel. There is also made the estimation of the total amount of Fe, detained in filter, which is 1313 g. It should be noted, according to the appearance and the detected concentration of Fe, its capacity has not been fully exhausted. This allows to receive additional information on the real filter resource, and to use it for solving the problems of filter mod- ernization.The studies have shown the possibility to estimate the amount and composition of impurities, which allows to be sure that this work is promising and possible to be integrated into the practical events to ensure the safe operation of civil aircraft. The publication aims to draw the attention of operators and regulatory authorities to the possibility of using the proposed method to provide a more reliable way of flight safety in civil aviation and to expand the university cooperation with the industry within dealing with this problem.

The organization of service production attributed to airports activity is analyzed. The importance and the actuality of information interaction problem solution between productive processes as a problem of organization of modern production are shown.Possibilities and features of information interaction system construction in form of multilevel hierarchical structure have been shown. The airport is considered as an enterprise aimed at service production where it is necessary to analyze much information in a limited timeframe. The production schedule often changes under the influence of many factors. This leads to the increase of the role of computerization and informatization of production processes what predetermines automation of production, creation of information environment and organization of information interaction needed for realization of production processes. The integrated organization form is proposed because it is oriented to the integration of different processes into a universal production system and it allows to conduct the coordination of local goals of particular processes in the context of the global purpose aimed at the improvement of the effectiveness of the airport activity. The main conditions needed for organization of information interaction between production processes and technological operations are considered, and the list of the following problems is determined. The attention is paid to the necessity of compatibility of structure and organization of interaction system in the conditions of the airline and the necessity of being its reflection in the information space of the airline. The usefulness of the intergrated organization form of information interaction based on information exchange between processes and service customers according to the network structure is explained. Multilevel character of this structure confirms its advantage over other items, however it also has a series of features presented in this work.

The article describes the history of navigation systems formation, such as "Cicada" system, which at that time could compete with the US "Transit", European, Chinese Beidou navigation system and the Japanese Quasi-Zenit.The detailed information about improving the American GPS system, launched in 1978 and working till now is provided. The characteristics of GPS-III counterpart "Transit", which became the platform for creating such modern globalnavigation systems as GLONASS and GPS. The process of implementation of the GLONASS system in civil aviation, itssegments, functions and features are considered. The stages of GLONASS satellite system orbital grouping formation are analyzed. The author draws the analogy with the American GPS system, the GALILEO system, which has a number of additional advantages, are given. The author remarks the features of the European counterpart of the GALILEO global navigation system. One of the goals of this system is to provide a high-precision positioning system, which Europe can rely on regardless of the Russian GLONASS system, the US - GPS and the Chinese Beidou. GALILEO offers a unique global search and rescue function called SAR, with an important feedback function. The peculiarities of Chinese scientists’ navigation system, the Beidou satellite system, and the Japanese global Quasi-Zenith Satellite System are described.Global navigation systems development tendencies are considered. The author dwells upon the path to world satellite systems globalization, a good example of which is the trend towards GLONASS and Beidou unification. Most attention was paid to the latest development of Russian scientists’ autonomous navigation system SINS 2015, which is a strap-down inertial navigation system and allows you to navigate the aircraft without being connected to a global satellite system. The ways of navigation systems further development in Russia are determined. The two naturally opposite directions are given, which are connected, on the one hand, with the Russian and Chinese symbiosis global navigation system, which will significantly simplify the interaction between the two countries and, on the other hand, with the creation of autonomous navigation system on each aircraft.

Modern aircraft are equipped with complicated systems and complexes of avionics. Aircraft and its avionics technical operation process is observed as a process with changing of operation states. Mathematical models of avionics processes and systems of technical operation are represented as Markov chains, Markov and semi-Markov processes. The purpose is to develop the graph-models of avionics technical operation processes, describing their work in flight, as well as during maintenance on the ground in the various systems of technical operation. The graph-models of processes and systems of on-board complexes and functional avionics systems in flight are proposed. They are based on the state tables. The models are specified for the various technical operation systems: the system with control of the reliability level, the system with parameters control and the system with resource control. The events, which cause the avionics complexes and functional systems change their technical state, are failures and faults of built-in test equipment. Avionics system of technical operation with reliability level control is applicable for objects with constant or slowly varying in time failure rate. Avionics system of technical operation with resource control is mainly used for objects with increasing over time failure rate. Avionics system of technical operation with parameters control is used for objects with increasing over time failure rate and with generalized parameters, which can provide forecasting and assign the borders of before-fail technical states. The proposed formal graphical approach avionics complexes and systems models designing is the basis for models and complex systems and facilities construction, both for a single aircraft and for an airline aircraft fleet, or even for the entire aircraft fleet of some specific type. The ultimate graph-models for avionics in various systems of technical operation permit the beginning of analytical models designing.

Currently, there is an increasing level of electrified equipment of aircraft. This work is performed under the concept of creating a Fully Electric Aircraft (FEA), where the functions of the individual aircraft systems (pneumatic and hydraulic) will be performed by an electrical power system. The result of these procedures will be a significant increase of the electric motor load on board the aircraft. Consequently, it will increase the energy sources power of the power supply system (PSS) of the aircraft. This work is devoted to mathematical modeling of the induction motor. The induction motor with the squirrel-cage rotor is considered. The models of electrical and mechanical parts were considered while obtaining the induction motor mathematical model. It allows considering the relationship of electromagnetic and electromechanical processes in transient and steady-state modes of motor operation. The electrical part model is implemented in the equations for the voltages of windings and flux linkages circuits of the induction motor, which are written in the system of phase coordinates "ABC". When considering the mathematical model of the mechanical part the equation of torques, influencing the induction motor shaft during rotating action was used. The matrix equations system is the mathematical model of the induction motor. As a result of solving those equations the authors have got the formulae for stator winding current phases and squirrel-cage rotor circuits of the induction motor. The obtained mathematical model describes the electromagnetic and electromechanical processes in the induction motor, in a stationary system of phase coordinates "ABC". This model, unlike models in rotating coordinates "dq", describes the processes in symmetric and asymmetric modes, such as phase failures (open-phase modes) and short-circuit phases of the induction motor, while the mathematical model implemented in the system of rotating coordinates "dq", is true only for symmetrical modes of motor operation.

In this article the authors consider the problem of simulating the process of a maintenance-free between scheduled maintenance aircraft system operational status changes, which failure during the flight leads to the disaster. On-board equipment with automatic self-repair between routine maintenance in the event the components fail is called maintenance-free. During operation, onboard equipment accumulates failures maintaining its functions with a safety level not lower than the required minimum. Trouble shooting is carried out either at the end of between-maintenance period (as a rule), or after the failure, which led to the functions disorder or to the decrease below the target level of flight safety (as an exception). The system contains both redundant and nonredundant units and elements with the known failure rates. The system can be in one of the three states: operable, extreme, failed. The excessive redundant elements allow the system to accumulate failures which are repaired during the routine maintenance. The process of system operational status changes is described with the discrete-continuous model in the flight time. Basing on the information about the probabilities of the on-board equipment being in an operable, extreme or failed state, it is possible to calculate such complex efficiency indicators as the average loss of sorties, the average operating costs, the expected number of emergency recovery operations and others. Numerical studies have been conducted to validate the proposed model. It is believed that maintenance work completely updates the system. The analysis of these indicators will allow to evaluate the maintenance-free aircraft equipment operation efficiency, as well as to make an effectiveness comparison with other methods of technical operation. The model can be also used to assess the technical operation systems performance. The model can be used to optimize the period between maintenance.

The development of new and modernization of existing aviation equipment specimens of different classes are accompanied and completed by the complex process of ground and flight tests. This phase of aviation equipment life cycle is implemented by means of organizational and technical systems - running centers. The latter include various proving grounds, measuring complex and systems, aircraft, ships, security and flight control offices, information processing laboratories and many other elements. The system analysis results of development challenges of the automated control systems of aviation equipment tests operations are presented. The automated control systems are in essence an automated data bank. The key role of development of flight tests automated control system in the process of creation of the automated control systems of aviation equipment tests operations is substantiated. The way of the mobile modular measuring complexes integration and the need for national methodologies and technological standards for database systems design concepts are grounded. Database system, as a central element in this scheme, provides collection, storing and updating of values of the elements described above in pace and the required frequency of the controlled object state monitoring. It is database system that provides the supervisory unit with actual data corresponding to specific moments of time, which concern the state processes, assessments of the progress and results of flight experiments, creating the necessary environment for aviation equipment managing and testing as a whole. The basis for development of subsystems of automated control systems of aviation equipment tests operations are conceptual design processes of the respective database system, the implementation effectiveness of which largely determines the level of success and ability to develop the systems being created. Introduced conclusions and suggestions can be used in the formation of R&D areas of activities to ensure the accelerated development of automated control systems of aviation equipment test operations on the base of subsystems conceptual models of database system.

Research in the field of aircraft development shows that from the point of view of sustainability and energy efficiency the most acceptable approach is the transition to all-electric aircraft (AEC). Electrification is aimed primarily on the aircraft most energy-intensive elements efficiency enhancing. Primarily these are power plant and air conditioning system. The actual problem discussed in this article is the development of methodology for the design of aircraft power complex with electric propulsion. The electric power plant literally extends the concept of aircraft power complex. The article considers two-level energy-informational design technology of the aircraft power complex. On the energetic level, the energy flows are optimized, and on the information level, the control laws that ensure restrictions compliance and loss minimization for a given level of entire system reliability are synthesized. From the point of view of sustainability and energy efficiency, the most acceptable is the transition to AEC. The proposed information-energy technique provides an opportunity to develop electric and hybrid aircraft with optimal weight and size and energy characteristics due to: electricity consumption timeline optimization through the redistribution of electric end users switch on moments, which provides a more uniform power mode, allowing the same set of electric users to reduce generator rated power, and as a result reduce the flight weight; manage a distributed system of electricity generation that provides the ability to use diverse energy sources; faul tsafety management based on rapid changes in the power network topology; energy recovery control; the sources, converters and users (input circuit) and power network real-time diagnostic operations.

The International Civil Aviation Organization (ICAO) regulates the need for issuance of special operators operating permits such as: for operations with the use of standards Reduced Vertical Separation Minimum (RVSM); Performance-based Navigation (PBN); auto landings on CATII CATIII ICAO categories; EDTO/ETOPS (Extended Twain OPerationS/Extended Diversion Time Operations) standards for the operation of turbine-powered airplane flights lasting more than 60 minutes to spare en-route with increased care at an alternate airfield and flight operations at the twin-engine plane over terrain without radio navigation; with the use of Traffic Alert and Collision Avoidance Systems (TCAS); with the use of Ground Proximity Warning Systems (GPWS) and with the use of Electronic Flight Bag (EFB). The ability to meet these requirements follows from the analysis of tactical, technical and operational characteristics of avionics, maintenance and repair programs (MRO), aircraft maintenance organizations (AMO) and a number of other factors. It should be based on a scientific approach and strict satisfaction of all requirements of legal and regulatory documents. The ability to use TCAS, EGPWS and EFB requires a comprehensive scientific analysis, taking into account all the operational factors. The article provides the performance of some scientific and practical aspects related to the application of the above mentioned standards and systems. Some modern methods of statistical analysis of the position and movement parameters of the aircraft are used. The possibility of more accurate estimates of the aircraft deviation in height and lateral deviation, as well as the decision on the conformity requirements for accuracy is shown.

The article considers the issues of civil aviation aircraft onboard computers data safety. Information security undeclared capabilities stand for technical equipment or software possibilities, which are not mentioned in the documentation. Documentation and tests content requirements are imposed during the software certification. Documentation requirements include documents composition and content of control (specification, description and program code, the source code). Test requirements include: static analysis of program codes (including the compliance of the sources with their loading modules monitoring); dynamic analysis of source code (including implementation of routes monitoring). Currently, there are no complex measures for checking onboard computer software. There are no rules and regulations that can allow controlling foreign production aircraft software, and the actual receiving of software is difficult. Consequently, the author suggests developing the basics of aviation rules and regulations, which allow to analyze the programs of CA aircraft onboard computers. If there are no software source codes the two approaches of code analysis are used: a structural static and dynamic analysis of the source code; signature-heuristic analysis of potentially dangerous operations. Static analysis determines the behavior of the program by reading the program code (without running the program) which is represented in the assembler language - disassembly listing. Program tracing is performed by the dynamic analysis. The analysis of aircraft software ability to detect undeclared capabilities using the interactive disassembler was considered in this article.

This article is devoted to mathematical modeling of the channel of AC on-board power supply systems (PSS) when running on static active-inductive load, connected on a "wye with neutral" and "delta". The mathematical model of aircraft synchronous generator, electricity distribution, three-phase static active-inductive load are considered. When making a mathematical description the author used the equations for the voltages of windings and flux linkages circuits of the stator and rotor of the generator in a stationary system phase coordinates "ABC". When considering the mathematical model of the distribution system, the equations that took into account the drop of the voltages on the active and inductive resistance of the distribution system power wires were used. When considering the mathematical models of three-phase static loads connected on a "wye with neutral" and "delta", the equations that took into account the drop of the voltages on the active and inductive resistance loads were used. The matrix equations system of channel PSS AC when running on a generalized three-phase static active-inductive load was obtained. The three phase static loads scheme connected according to the "delta" scheme was converted to "wye" to simplify the solution of channel PSS AC circuit matrix equations system. The choice of the phase coordinates system "ABC" for the mathematical description of the generator, distribution system and the static load was made due to its advantage over the coordinate system "dq", because the equation written in phase coordinates are valid for symmetric and asymmetric modes of the generator, while the equations written in the coordinate system "dq" will be valid only for symmetric modes. As a result of joint solution of the generator equations, distribution system, three-phase static loads there were obtained the formulae for the generator stator winding phases, generator phases currents, the voltage drops on the load phases and load phases currents connected on a "wye with neutral" and "delta".

One of the promising ways to boost the gas turbine engine is to install a pulse detonation module in the exhaust case. Research on the effectiveness of the developed module in the expenditure thermal vacuum chamber, providing a complete simulation of these terms and conditions, requires unique equipment, as well as the significant financial and oper- ating costs. Accordingly ,it is more efficient to conduct performance and effectiveness assessment of the pulse detonation module using the existing test rigs, modified to partially simulate flight conditions comprising: a platform with the studied gas turbine engine (GTE), a power plant on a movable platform, pressurization system pipeline from an auxiliary power unit (APU) to the test engine, fuel and electrical systems of the test rig. The article presents small-size GTE pressurization system design results. The pipeline design is based on the conditions of mutual arrangement of the studied GTE and APU test cell. The choice of design solutions for production and assembly of components of the pressurization system, and the results are presented algorithm and calculating geometrical parameters ejector providing the required pressure and air flow temperature at the inlet to the studied engine. As a result, the research reasonably determined the structural diagram of the boost system test rig, providing a partial simulation of flight conditions at the inlet to the small-sized turbine engine. There were defined the necessary geometry and gas-dynamic properties of the gas ejector, the use of which as part of test rig pres- surization system will start the series of studies, according to the pulse detonation performance of the module.

The article continues the aviation electro mechanics drive-generating aggregate structure research and aims to form the recommendations for getting the best possible combination of operating performance of such aggregate. Using the motoring of asynchronous machine on the first stage and the circulation of active-power related to it in the aggregate con- tour require synchronous generator over motoring in proportion to the required shaft speed rotation of the generator. Due to the difficulty to provide the required value of asynchronous machine moment, when starting it with AC or DC, one should give preference to the asynchronous brake (in this case the necessity for the source of direct-current is eliminated and the scheme realization of the mode is simplified). The development of differential asynchronously-synchronous drive- generating aggregate with three generator stages of asynchronous machine allows decreasing the value of synchronous generator electromagnetic power, to provide the high average value of aggregate performance efficiency. Applied to mod- ern turbo-engines which continuous work is only possible at certain fixed rotation speed, the number of generator aggregate operational stages and operation modes of asynchronous machine need to be chosen in order to provide the best possible indexes exactly at these speeds, assuming the relatively large values of losses at brief transient operational modes of aircraft engine. The calculation series results of power performance of aviation electro mechanics asynchronously-synchronous drive-generating aggregate are presented in the article. On the basis of these results the author could give the recommenda- tions for aggregate structure and operational modes choice for asynchronous machine optimization. The development of drive-generating aggregate with three generating steps of the asynchronous machine allows to reduce its specific weight due to the value of estimated electromagnetic power of the synchronous generator.

The current state of the onboard systems is characterized by the integration of aviation and radio-electronic equipment systems for solving problems of navigation and control. These problems include micro-navigation of the anten- na phase center (APC) of the radar during the review of the Earth's surface from aboard the aircraft. Increasing of the reso- lution of the radar station (RLS) by hardware increasing the antenna size is not always possible due to restrictions on the aircraft onboard equipment weight and dimensions. Therefore the implementation of analytic extension of the radiation pattern by "gluing" the images, obtained by RLS on the aircraft motion trajectory is embodied. The estimations are con- verted into amendments to the signals of RLS with synthetic aperture RSA to compensate instabilities. The purpose of the research is building a theoretical basis and a practical implementation of procedures for evaluating the trajectory APS in- stabilities using a distributed system of inertial-satellite micro-navigation (DSMN) taking into account the RSA flight oper- ations actual conditions. The technology of evaluation and compensation of RSA trajectory instabilities via DSMN is con- sidered. The implementation of this technology is based on the mutual support of inertial, satellite and radar systems. Syn- chronization procedures of inertial and satellite measurements in the evaluation of DSMN errors are proposed. The given results of DSMN flight testing justify the possibility and expediency to apply the proposed technology in order to improve the resolution of RSA. The compensation of aircraft trajectory instabilities in RSA signals can be provided by inertial- satellite micro-navigation system, taking into account the actual conditions of the RSA flight operations. The researches show that in order to achieve the required resolution of RSA it seems to be appropriate to define the rational balance be- tween accuracy DSMN characteristics and RSA wavelength range.

Traditionally, the problem of autonomous navigation is solved by dead reckoning navigation flight parameters (NFP) of the aircraft (AC). With increasing requirements to accuracy of definition NFP improved the sensors of the primary navigation information: gyroscopes and accelerometers. the gyroscopes of a new type, the so-called solid-state wave gyroscopes (SSVG) are currently developed and put into practice. The work deals with the problem of increasing the accuracy of measurements of angular velocity of the hemispherical resonator gyroscope (HRG). The reduction in the accuracy characteristics of HRG is caused by the presence of defects in the distribution of mass in the volume of its design. The synthesis of control system for optimal damping of the distortion parameters of the standing wave due to the influence of the mass defect resonator is adapted. The research challenge was: to examine and analytically offset the impact of the standing wave (amplitude and frequency) parameters defect. Research was performed by mathematical modeling in the environment of SolidWorks Simulation for the case when the characteristics of the sensitive element of the HRG met the technological drawings of a particular type of resonator. The method of the inverse dynamics was chosen for synthesis. The research results are presented in graphs the amplitude-frequency characteristics (AFC) of the resonator output signal. Simulation was performed for the cases: the perfect distribution of weight; the presence of the mass defect; the presence of the mass defects are shown using the synthesized control action. Evaluating the effectiveness of the proposed control algorithm is determined by the results of the resonator output signal simulation provided the perfect constructive and its performance in the presence of a mass defect in it. It is assumed that the excitation signals are standing waves in the two cases are identical in both amplitude and frequency. In this case, if the output signal of the compensating effects should coincide with the ideal signal at the most.