ΠšΠ°Ρ‚Π΅Π³ΠΎΡ€ΠΈΡ: Aeronautics

Analysis of diagnostic techniques for aircraft aerometric systems with the use of data recorders

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UDK 629.7 BBK 39.56

Shomankov D. A.

Potapov I. A.

Korshak S. A.

The article contains some results of the analysis of diagnostic models and techniques for defining the dynamic errors in indications (measurements) of flight altitude and speed parameters caused by lag (delay) of pressure transmission in the lines of the pitot probe systems. Their essential drawbacks are revealed and the ways of their elimination are defined.

Key words: dynamic error, pneumatic circuit, pressure, temperature, delay, aerodynamic correction, delay coefficient.

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Reduction –based increase of robustness of a neural-net model of gas-turbine engine monitoring

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UDK 621.438, 004.855 BBK Π—363.3, 32.813, 22.18

Novikova S. V.

Kremleva J. Sh.

The article presents a technique of increasing the robustness of a neural-net model of gas-turbine engine monitoring during stand tests due to decreasing the number of insignificant links in the neural network (neural network reduction). The technique is based on converting the problem of neural network learning into that of multi-criteria optimization which includes the error minimization criterion and the criterion of minimizing the absolute values of the weight links of a neural network. The latter requirement leads to reveal of insignificant links which can be deleted without any loss of accuracy. As a result, the ability of the model to summarize increases greatly, robustness increases as well, the calculation error of monitored parameters decreases.

Key words: model robustness, neural networks, stand tests, monitoring of a gas-turbine engine, reduction of a neural network.

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A proposal to modernize the SSJ 100 onboard maintenance system

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UDK 629.7.05 BBK 39.56

Cavvina A. M.

The need for an onboard maintenance system on modern civil airplanes is caused by the increasing number of flights and the reducing parking period.Β  The operation speed of an onboard maintenance system greatly influences the efficiency of aircraft operation, the time to reveal and eliminate a failure being considerably reduced. The flight safety increases as well. The economic expenditures of airlines for additional ground service vehicles are reduced.

Key words: onboard maintenance system, maintenance, SSJ 100, Superjet.

Download article in PDF 617.2 kB

The automation systems of surveillance and control of aerodrome traffic and air traffic management based on ADS-B

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UDK 351.814.33 BBK 39.57-5

Knyazhskiy A. Yu.

Plyasovskikh A. P.

Shcherbakov E. S.

An equipment of functional augmentation automatically dependent surveillance-broadcasting are encouraged to include in the automation systems of surveillance and control of aerodrome traffic and automation systems of air traffic control. This augmentation to the equipment complexes allows estimating the error of the coordinates issued automatically by dependent surveillance – broadcasting and to compensate in case of its slow changing. The information from the satellite radio navigation system is not taken into account in case of a rapid change in the error characteristics which are not allowing for sufficiently accurate compensation.

Keywords: SRNS, ADS-B, error, aircraft movement, air traffic control, automation.

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Improving the estimation procedure of the residual operation life of a bypass turbojet

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UDK 629.5.03-843.8 BBK 74.5

Karavaev Y.A.

Hodackij S.A.

The article presents general approaches to forming an estimation procedure of the residual operation life of the bypass turbojets operated on civil aircraft for long periods of time by taking actual operating conditions into account. With the example of D-436-148 aircraft engine having the standard control program the authors analyze how the size of turbine-blade tip clearances influences the rate of exhaustion of a bypass turbojet module – the gas turbine. A fraction of moving blade damage on takeoff is proposed to be used as a parameter defining the rate of exhaustion of the gas turbine.

Key words:Β gas-turbine engine lifetime, turbine-blade tip clearances, durability of moving blades, creep.

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The helicopter cockpit training simulator of MI-8t based on the aircraft simulator

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UDC 378.162.33 BBK 39.5

V. M. Popov

S. V. Zdrachuk

The application of aircraft simulator X-plane for simulating flight dynamics and Arduino hardware environment for creating control system simulators, instrument and flight navigation equipment during the development of the cockpit of Mi-8T simulator is presented in the article.

Keywords: aircraft simulator, training aircraft simulator, Arduino hardware environment

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Influence of GTE rotor vibrations on technical condition of inter-shaft bearing

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UDC 004. 588 BBK 74.5

Yu. A. Karavaev

S. A. Khodatskiy

A significant number of aircraft engines taking out early from operation are associated with inter-shaft bearing failures. Possible causes of such failures are violations of their lubrication and cooling conditions. The article presents the results of experimental studies to assess the effect of reducing the performance of the oil tube with bending vibrations of the rotor on the thermal state of the inter-shaft bearing.

During the turbofan engine operation, its shaft co-performs bending vibrations due to the imbalance of the rotor. In this case, the oil tube, placed inside the engine shaft, will also make bending vibrations, which can be one of the reasons for reducing oil consumption through the oil tube with a significant level of vibrations. In this case, the working temperature of the inter-shaft bearing may increase significantly.

Keywords: aircraft engine, inter-shaft bearing, vibration velocity, bearing temperature, GTE oil system parameters.

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Comparative analysis of a mathematical model of the turbine gas temperature sensor of the turbocharger of a helicopter gas-turbine engine based on regres-sion analysis and neural networks

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UDK 629.7:681.324 BBK 39.551-01-07 S21

A. A. San’ko

A. A. Shejnikov

The article presents the results of a comparative analysis of mathematical models of the turbine gas temperature sensor of the turbocharger of a helicopter gas turbine engine based on regression analysis and on a multilayer neural network. The inexpediency of using a multilayer neural network as a mathematical model of a gas temperature sensor is proved. The optimal type of the mathematical model of the gas temperature sensor is selected by the criterion of the minimum error of the output parameter calculation.

Keywords: gas turbine engine, rotor, mathematical model of gas temperature sensor, helicopter, neural network.

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The influence of quasi-sinusoidal inhomogenuities on the characteristics of double- and three-hop ionospheric reflections

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UDC: 621.371.33 BBK 39.57

A.I. Agaryshev

Nguyen Minh Giang

M.A. Portnov

The article presents the results of researching the influence of ionosperic inhomogenuities on the maximum observed frequency (MOF) and the angles of arriving the radiowaves reflected two and three times from the ionosphere (2F2 and 3F2 modes). The authors present the calculated МOF and angles of arrival of decameter radio waves using the method of equal MUF under conditions of quasi-sinusoidal inhomogenuities. The results of calculations are compared with the results of measurements.

Keywords: maximum usable frequency, maximum observed frequency, inhomogeneity of the electron concentration, characteristics of double- and three-hop ionospheric reflections,Β  the angles of arrival of 2F2, 3F2 modes.

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Analysis of the influence of aerometric instruments and pitot – static probes faults on flight safety

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UDK 629.7 BBK 39.56

A. Shomankov

The main types of failures and faults of pitot – static probes and aerometric instruments are determined and the causes of their occurrence are revealed. The results of the analysis of these faults influence on flight safety are presented.

Keywords: faults, mean flight time between failures, aviation event, difficult situation, probability of occurrence inflight abnormal circumstances, air crash, accident.

Download article in PDF 190.0 kB

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