The paper shows possibility to use Paris-Erdogan equation for simulation of fatigue crack growth under random loading. In the considered equation effective stress intensity factor range was introduced. The introduced methodology for crack growth simulation is based on the concept of a “basic” random loading. The discussed methodology included consideration of overloads influence on the fatigue crack growth. The theoretical models are based on the experimental researches of fatigue crack growth under random loading that have realized during specimens fatigue tests of two Al-based alloys (D16АТ - the same as 2024-T3, and В95АТВ - 7075-T6). In all cases the random loading has been considered as Gaussian processes of cyclic loading with introduced and discussed parameters of the investigated processes.

The paper shows the possibility of using Paris-Erdogan equation for simulation fatigue crack growth under random loading. The considered equation has introduced the effective stress intensity factor range. The introduced methodology for crack growth simulation is based on the concept of a “basic” random loading. The discussed methodology included consideration of overloads influence on the fatigue crack growth. The theoretical model is based on the experimental researches of fatigue crack growth under random loading that have been realized during specimens fatigue tests of two Al-based alloys (D16chАТ - the same as 2024-T3, and В95АТВ - 7075-T6). In the tests the specimens of a center cracked panel were used. In all cases the random loading has been considered as Gaussian processes of cyclic loading with introduced and discussed parameters of investigated processes. As a result of investigations the model for estimation crack growth period in the different random of irregular cyclic loads was introduced.

Investigations and tests of specimens of VT3-1 titanium alloy were done in Very-High-Cycle-Fatigue regime. Specimens were manufactured from compressor disks of D30-KU engine, and tests under frequency 20 kHz performed on the special test-bed in laboratory of Paris University «ITMA». Crack origination takes place subsurface from different material structural inhomogeneities. Fatigue origin has fine-granular area in the case of specimen tests under symmetrical cycle of cyclic loads but in the case of cyclic tension, origin has flat facet because of a-phase splitting. Experimental data dispersion under the constant stress level covered three orders.

The paper deals with a new approach to an estimation of level of working capacity and quality of a difficult technical plant functioning.

The paper deals with a new approach to an estimation of working capacity and quality of functioning of electronic system of an aircraft power-plant automatic control.

The synthesis method of the functional structure hydraulic systems are deal with in the paper. The method is based on the representation of synthesis objects as a control system in relation to the working environment as an object management. Synthesis provides the procedures for formalizing the functional requirement in a matrix of numerical codes and their decomposition to the level of function elements. The method is addressed to specialists in computer-aided projecting of hydraulic systems for various applications, including systems of water supply, refueling, fire systems, etc.

The calculation procedure for numerical simulation of the swirled flow of the incompressible viscous fluid in the cylinder with rotating bases is presented. Different flow regimes and the corresponding recirculating zone evolution are investigated for the cylindrical domains with small heights.

The analysis of failures for the unit components has been presented in the paper. Specifying the possible failure of technical object components and units under operation that can cause catastrophic consequences and basing on statistics the authors have offered the estimation criteria for anthropogenic risk measure.

Method of exhaust jet flux interaction with deflecting shield computer modeling is proposed in this article. The article is devoted to concrete ecological task - to decrease the noise influence on ground maintenance stuff and passengers in the airports. The method is based on the Reynolds equation system solution obtained with the help of control volume method. Calculation results give an opportunity to choose main deflecting shield parameters according to concrete airport conditions.

In the article some equations are derived to establish the relationships between the thermodynamic cycle parameters applying to bypass engines with separate exhaust nozzles. Necessary calculations are made and the main dependences are analyzed. Some of them have not been analyzed in the famous articles.

The article deals with algorithmic and software, which have been developed for research of communications of parameters, registered in systems of various nature. Distinctive feature of a realized way of research is reception of the decision of tasks of multidimensional statistics not on static sample, but on set consecutive data that corresponds to dynamic character of real systems.

This paper covers one stress intensity factor calculation method for the blades of the turbojet.

This article discusses the results of current research on the impact of wind on the work of the engines PS-90A on the mileage of the IL-76td-90 with the use of reverse thrust.

The article describes a method formation of prospective appearance of transport aircraft, based on the forecast of development of the freight market. An analysis of the statistical characteristics of the goods transported, the concept of utilization volume aircraft to analyze the efficiency of use of transport cabin, a comparison of existing types of transport aircraft vehicle cabs.

The article discusses the use of a probabilistic model for simplified assessments required reserves reliability control (crack detection probability). Ratios and charts for estimating reliability coefficients of the probability of detection of a fatigue crack are given. The use of safety factors equal to 2 ... 3 possible with a high quality of diagnosis (probability of detecting fatigue crack greater than 0.95) is shown.

This article is dealing with the research of bootstrap adaptation during initial air-jet engine parameters processing in trend analysis. Types of bootstrap and its adaptation are shown. Optimal bootstrap variation length is chosen. Bootstrap-method is compared to active methods.

This article has a purpose to give a brief review of usage of composite materials in the structure of modern civil aircraft. The current condition of civil aviation was analyzed, serious problems were determined and possible achievements in the future were discussed. Advantages and disadvantages of composite materials were analyzed, non-destructive methods of control were reviewed and the necessity to design new method, which allows to control the integrity of structure in real time during design service goal of the aircraft (the concept of “clever material”) was shown.

The use of thermovision technology to diagnose failure of the combustion flame test tube of the main combustion chamber gas turbine engine is deal with in the article. Join the thermal radiation of the jet of combustion products and the internal elements was carried out using short-wave thermovision system AGA-782 with spectral spectral filters in several ranges from 3.2 to 5.6 microns. Thermovision is mounted on the axis of the flame tube. The output signal was recorded and processed on a computer in real time, allowing monitor the combustion process and the thermal state of the object during the experiment.

The article deals with identification and shows examples on parametrical diagnosing of GTE on the same aircraft using synchrony and asynchrony of time series.

This article deals with, results which are shown using K-Means as a tool for diagnosis of Aircraft engine condition.

In article results of researches are presented according to efficiency of application of adaptive algorithm of management by the maneuverable plane realised in a cross-section control path, on the basis of identification of some aerodynamic characteristics of the plane and the indignations caused by formation by an asymmetrical configuration of placing of external suspension. By modelling of movement of the plane during performance S - figurative maneuvers with use of a programmno-modelling complex and the flight stand substantial improvement of characteristics of controllability of the asymmetrical plane and, thus, increase of efficiency of its application is shown.

A brief overview of the strategic planning documents in the aviation industry, defined the legal status of the developed "National Plan for Science and Technology in the aircraft industry for the period up to 2025 and the subsequent prospect" assesses its role and place in the strategic planning documents, the relationship with the main documents. Disclosed structure of the National Plan and the goal of scientific and technological potential, defined by the National Plan.