Budkov A. S.

Neretin E. S.

The work is devoted to the analysis of problems in performing the four-dimensional routes, as well as the development of the architecture of a decision support system for simplified procedures of flying in emergency situations during the flight. The developed architecture allows the crew to be provided with the necessary information for decision making in instrument meteorological conditions as well as in conflict situations with other air traffic participants.

Key words: Civil aircraft, integrated modular avionics, flight management system, 4-D navigation, decision support system.

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Lituev N. A.

Savelev A. S.

Neretin E. S.

Integrated flight control system of a civil aircraft safety requirements validation process using means of model-based design is considered. The necessity for correct Functional Hazard Assessment is explained. Hardware and software needed for the problem are described. Complex mathematical model structure and human machine interface are provided.

Key words: model-based design, control systems, flight safety, requirements validation.

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Brusnikin P. M.

Dudkin S. O.

Neretin E. S.

The paper analyzes the concepts of avionics, the principles of creating complexes of avionics equipment and existing analogues of on-board maintenance systems (OMS). The architecture of the OMS, its functional software and hardware for civil aircraft is proposed. OMS developed on the basis of integrated modular avionics (IMA) will allow you to unload the cable network of the aircraft, increase the reliability of the system as a whole, and simplify the work with OMS for the ground maintenance personnel.

Key words: civil aircraft, integrated modular avionics, on-Board Maintenance System, distributed architecture, avionics.

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Savel’ev A. S.

Neretin E. S.

The main purpose of civil aviation is to provide economical, reliable and safe flying. The integrated (fly-by-wire) control system and autopilot system are among the most important aircraft systems. The fly-by-wire control system includes, among other things, controls in the cockpit – yokes (Boeing) and side sticks (Airbus, Irkut, Sukhoi). The side sticks are nowadays a priority in cockpit controls development due to increase of cost-effectiveness compared to the yokes. The rigidly connected yokes provide force feedback for the pilots both in automatic and in manual control modes.   When using the side sticks the pilot has no force feedback because there are no mechanical connections. This has a negative influence on flight safety.  To solve the problem active side sticks are being developed and implemented nowadays. The active side sticks are not certified for any large civil airplanes. The aim of the paper is to give a preliminary assessment of safety of tracking the autopilot signals by the active stick in accordance with   SAE ARP 4761 and SAE ARP 4764A recommendations.

Key words: active controls, control systems, flight safety, fault tree analysis, assessment of functional hazards.

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UDK 681.518.3 BBK 39.56

Mamkin E. M.

Krytsin A. V.

Ilyashenko D. M.

Dyachenko S. A.

Neretin E. S.

The authors analyzed the existing means of automation of verifying the software of aircraft onboard equipment. As the result they developed a software application which automates verifying the electronic display systems of modern and advanced civil airplanes as well as a testing technique for its use. The proposed solution allows reducing time and financial costs of system testing.

Key words: civil airplane, avionics, software, verification, image recognition, neural network.

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UDK 681.518.3 BBK 39.56

Dyachenko S. A.

Chufirin V. A.

Neretin E. S.

The paper presents the analysis of design principles for avionic complexes as well as for modern systems of indication in the cockpit. The authors developed the architecture of the head-up display system for advanced civil transport airplanes based on the concept of integrated module avionics. The applied approach allows shortening the time spent for development, tests and certification of an airplane as well as reducing the cost of aircraft operation and its weight and size.   

Key words: civil airplane, integrated module avionics, information presentation systems, systems of technical imaging, head-up display.

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UDK 621.391:621.396 BBK 39.57-5 S66

Skrypnik O. N.

Arefyev R. O.

Arefyeva (Astrakhanceva) N. G.

The Global Navigation Satellite Systems `(GNSS) such as GLONASS (Russia) and GPS (the USA) systems find wide application in different fields including aviation. The growing demands of different users’ groups for accuracy and reliability of positioning can be met by solving a navigational problem with the use of all visible satellites which belong to different systems. This function was implemented in combined GNSS receivers, the research of performance features and positioning error characteristics of combined GLONASS/GPS receivers under different conditions of use and in different operational modes being relevant. The paper contains the results of natural experiments for investigation of positioning accuracy characteristics carried out with Geos-1M receiver. The experiments were performed in urban settings and in open terrain, in GLONASS and GPS operation modes of the receiver as well as in GLONASS/GPS combined mode. The experimental results were analyzed with the help of special software and algorithms of statistical manipulation. The obtained results allow assessing the main statistical characteristics of positioning errors and operational efficiency of the combined GNSS receiver under different conditions and in different operational modes. It can be used in practice for selecting a more efficient operational mode of the combined receiver for given conditions as well as for validating mathematical models of the positioning errors of SNS receivers.

Keywords: global navigation satellite system, GNSS, combined GNSS receiver, positioning accuracy.

*This work was supported by the Russian Foundation for Basic Research (Grant No. 19-08-00010 A).

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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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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.  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.

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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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