Ergonomic analysis of the effects of the introduction of electronic displays in the cockpits of light single-engine piston aircrafts

This paper sublimates previous experience and results of certain studies related to the introduction of glass cockpit(GC) in the light piston aircraft.It considers the influence of the replacement of analog, conventional displays with the glass cockpits, on the safetyof thelight piston aircrafts, primarily from the aspect of reducing human (pilots) errors. Certain design solutions that were proposed with the introduction of the new technology in the light aviation are evaluated, including also into the consideration the results of studies that have not confirmed the expected increase of safety, in comparison with airplanes equipped with the conventional instruments

Measurement and analysis of vibrations of the axial-flow compressor caused by inlet flow instability during the flight of aircraft

U radu je prezentovan praktičan primer merenja i analize vibracija na prva dva stepena aksijalnog kompresora sa namerom da se proceni povezanost između poremećene ulazne struje vazduha i pojave otcepljenja strujnica od lopatica kompresora. Poremećenost ulazne struje vazduha je ispitivana tokom različitih režima leta aviona sa maksimalnim potiskom, pod pretpostavkom da postoji nesimetrično strujanje vazduha kroz dvostruki uvodnik i da ono ima uticaj na pojavu vibracija kompresora. Prikazano je merenje vibracija na avionu Galeb G-2 sa motorom Rolls Royce Viper Mk22-6 sa ciljem da se prepozna i definiše minimum neophodnih podataka koji bi ukazali na potencijalnu poremećenu struju vazduha kroz kompresor, kao posledicu nejednake raspodele vazdušne struje u uvodniku. Efikasnost ove metodologije merenja predstavljena je korišćenjem Furijeovih transformacija. Predložena metodologija merenja i analize može se sprovoditi na različitim tipovima aviona u cilju istraživanja pojave otcepljenja strujnica i pumpanja kompresora.This paper presents a practical example of the measurement and analysis of vibrations in the first two stages of the axial-flow compressor with intention to estimate a connection between inlet air flow distortions and appearance of stalling of the compressor blades. The inlet air flow distortions were tested during different regimes of the aircraft flight with a maximum thrust, with an assumption that the asymmetry of air flow through the twin-inlets existed and had effect on vibrations of the compressor. The paper shows the measurement of vibrations on the Galeb G-2 aircraft powered by the Rolls Royce Viper Mk22-6 engine with the aim to recognize and define the minimum necessary data for detection of the potential distorted air flow through the compressor, as consequences of an unequal air flow distribution in the inlets. The detection capability of this methodology of measurement is presented using the fast Fourier transform (FFT). The proposed methodology of measurement and analysis can be implemented in different types of aircraft in order to research the occurrence of stall and surge

Measurement and analysis of vibrations of the axial-flow compressor caused by inlet flow instability during the flight of aircraft

U radu je prezentovan praktičan primer merenja i analize vibracija na prva dva stepena aksijalnog kompresora sa namerom da se proceni povezanost između poremećene ulazne struje vazduha i pojave otcepljenja strujnica od lopatica kompresora. Poremećenost ulazne struje vazduha je ispitivana tokom različitih režima leta aviona sa maksimalnim potiskom, pod pretpostavkom da postoji nesimetrično strujanje vazduha kroz dvostruki uvodnik i da ono ima uticaj na pojavu vibracija kompresora. Prikazano je merenje vibracija na avionu Galeb G-2 sa motorom Rolls Royce Viper Mk22-6 sa ciljem da se prepozna i definiše minimum neophodnih podataka koji bi ukazali na potencijalnu poremećenu struju vazduha kroz kompresor, kao posledicu nejednake raspodele vazdušne struje u uvodniku. Efikasnost ove metodologije merenja predstavljena je korišćenjem Furijeovih transformacija. Predložena metodologija merenja i analize može se sprovoditi na različitim tipovima aviona u cilju istraživanja pojave otcepljenja strujnica i pumpanja kompresora.This paper presents a practical example of the measurement and analysis of vibrations in the first two stages of the axial-flow compressor with intention to estimate a connection between inlet air flow distortions and appearance of stalling of the compressor blades. The inlet air flow distortions were tested during different regimes of the aircraft flight with a maximum thrust, with an assumption that the asymmetry of air flow through the twin-inlets existed and had effect on vibrations of the compressor. The paper shows the measurement of vibrations on the Galeb G-2 aircraft powered by the Rolls Royce Viper Mk22-6 engine with the aim to recognize and define the minimum necessary data for detection of the potential distorted air flow through the compressor, as consequences of an unequal air flow distribution in the inlets. The detection capability of this methodology of measurement is presented using the fast Fourier transform (FFT). The proposed methodology of measurement and analysis can be implemented in different types of aircraft in order to research the occurrence of stall and surge