Mariusz Michalski

Branża lotnicza jest odpowiedzialna za zapewnienie bezpieczeństwa samolotów i ich pasażerów. Systemy sygnalizacji pożaru działają niezawodnie, zapewniając bezpieczeństwo lotów. Fałszywe alarmy mogą jednak stanowić poważne wyzwanie, prowadząc do niepotrzebnych zakłóceń i potencjalnie zagrażając skuteczności środków ochrony przeciwpożarowej. Niniejszy przegląd literatury ma na celu zbadanie przyczyn i konsekwencji fałszywych aktywacji lotniczych systemów przeciwpożarowych spowodowanych zwarciami w blokach sterowania. Niniejszy artykuł koncentruje się na analizie uszkodzeń systemu przeciwpożarowego samolotu transportowego. Analiza budowy i działania płytki wzmacniacza pozwoliła na wyznaczenie schematu elektrycznego (w tym identyfikację wartości elementów elektronicznych) oraz opracowanie jego numerycznego odpowiednika w pakiecie obliczeniowym Circuit-Maker (umożliwiającym projektowanie i testowanie obwodów elektrycznych, w tym obrazowanie przebiegu napięć i prądów w stanach dynamicznych). Wyniki symulacji komputerowych i badań weryfikacyjnych posłużyły do diagnostyki systemu SSP-FK podczas badania wybranych przypadków jego samoistnych zadziałań.

This article is focused on the research concerning the calculation of the durability of electrical machines installed in the electrical system of M-28 and C-130 Hercules aircraft. The article presents a method of predicting the service life of aircraft commutator machines, which are the primary source of electrical energy. The result of the research was the determination of the durability of bearings and coils of electrical machines operated on aircraft based on a flight profile analysis. It is problematic to directly measure the wear of bearings and windings of an electric machine on the aircraft. Their usage can be determined from the relation between their wear and the ambient temperature. This research can be used in practice to plan maintenance work on the analyzed aircrafts.

Introduction: Although aviation is considered the safest mode of transportation, the annual number of pilots blinded by laser light cannot be understated. An analysis of the available statistics indicates that it is a widespread phenomenon. The stories told by the pilots show the consequences of these incidents, ranging from temporary sight loss to months of vision problems. The article also describes the current penalties for dazzling a pilot by laser light. Moreover, limited research has been conducted on the intensity of laser light of different wavelengths passing through the fairing and through standard glasses used by pilots. Understanding the effects of laser glare on pilots can help reduce adverse events and improve the ability of safety managers to develop safety procedures. Correctly designed transport systems enable effective route planning and order processing. Methods: Two types of easily available laser pointers, drawn at different distances from the aircraft, were analyzed and the intensity of the transmitted light was examined. Results: The results showed that the intensity decreases with distance and that the intensity is too low to harm the eye. In addition, it should not be forgotten that the light propagates in a cone which strengthens the illumination effect in the cabin and causes pilots to lose orientation. Practical application of the findings: They enable the identification of areas around the airport where the use of lasers should be prohibited. Practical Application: The possibility of determining the transition of laser light through the windscreen of the aircraft as well as its intensity under near real-life conditions.

The article describes the method of predicting the reliability and durability of an aircraft commutator, which is a primary source of electric energy in helicopters. Tests were conducted for 10 starter-generators. From this research it follows that the technical condition of brushes and bearings has a significant impact on the reliability of starter-generators. The reliability of starter-generators was determined based on the method consisting of two stages that was adopted: the first stage involved determining the density function of changes in diagnostic parameter depending on the operating time, but the second stage included the assessment of the reliability of bearings of the starter-generator taking into account the real flight profile. The first stage of the adopted method consisted of defining the dynamic model of changing the length of the starter-generator’s brush, which became the probabilistic model. Subsequently, based on differential equations, Fokker–Planck partial differential equation was derived, which describes the process of increasing the brush wear in a probabilistic way. This method enables the prediction of the residual durability of the helicopter’s starter-generator due to the change in a diagnostic parameter which is the wear of brushes during starter-generator operation. The second stage of this method allows determining the durability of starter-generator’s bearings building upon the average helicopter’s flight profile. Owing to the difficulty in measuring the wear of bearings, the relation between the durability of bearings and the temperature of surroundings can be applied by replacing the flight altitude with temperature. The reliability of the helicopter’s starter-generator was determined based on the serial-type reliability structure.

The method of the stochastic Markov process used for the analysis of operation of a training aircraft-Cessna 150 was presented in the article. In this article, the time changing probability of readiness was determined on the basis of knowledge of the current aircraft operation. Markov stochastic processes have been used as a model to determine aircraft-Cessna 150 readiness for specific tasks. In order to determine the readiness, the probability of being in one of the investigated states is determined. The analysed states included: standby, pre-flight service, flight, interstate service, after-flight service and hangar service.