SELECTED CHARACTERISTICS OF THE ELECTRIC PROPULSION SYSTEM OF AIRCRAFT AS FOUND OUT FROM THE GROUND-BASED LABORATORY TESTS

The paper is a discussion on ground-based laboratory tests of the aircraft’s electric propulsion system. The tests were intended to find relationships between environmental conditions and characteristics of the aircraft electric motor. The object under examination was a brushless DC motor AXI 2820/14 of 360 W power. Presented and discussed is the AFIT-made test bench that enables suitable, pre-planned experiments to be carried out. Discussed are also procedures of taking measurements of electric motor characteristics, followed with discussion of results. Presented selected issues of parametric description of gained results. With measurements as the basis, the relationships, first, between the electric motor’s efficiency and temperature, and second, between both the applied power and the power output (effective power) and the ambient temperature have been found. The most important findings of the testing work are, first, that the pressure does not affect the characteristics of the electric motor’s performance and second, determination of how temperature affects these characteristics. The results gained have formed the basis for the most vital flight parameters of electrically driven aircraft to be found, including the energy consumption essential for the flight range and endurance. All these findings give grounds for standardization calculations that consist in recalculation of characteristics determined in the course of aircraft flight-testing. Because of their representativeness, they also prove good illustrative examples to demonstrate properties of aircraft’s electric propulsion system

Flight tests of real operational loads in elements of the SU-22UM3K aircraft strukture

W pracy przedstawiono autorski system pomiarowo-rejestrujący do zbierania informacji o obciążeniach eksploatacyjnych występujących w elementach struktury samolotu Su-22UM3K. Badania obciążeń w wybranych elementach konstrukcji płatowca samolotu Su-22UM3K przeprowadzono z wykorzystaniem systemu pomiarowego KAM-500. W opracowaniu systemu wykorzystano modułową budowę co pozwala na zmianę konfiguracji systemu zgodnie z potrzebą zadania pomiarowego. Badania w locie obciążeń obejmowały elementy zadań występujące w programie szkolenia lotniczego na samolocie Su-22UM3K w celu dostarczanie informacji o rzeczywistym profilu eksploatacji oraz określenie reprezentatywnych tensometrycznych kanałów pomiarowych w dalszej eksploatacji samolotu.The paper has been intended to present an original measuring-and-recording system to collect information on service loads that arise in structural components of the Su-22UM3K aircraft. Research work into loads in some selected structural components of the Su-22UM3K has been carried out with the KAM-500 measuring system applied. Modular design has been used to develop the system. This, in turn, allows of changes in the system’s configuration, according to what a measuring task requires. The flight testing of loads has covered items of tasks included in the flying training program for the Su-22UM3K to collect/deliver data on an actual service profile and to determine representative straingauge measuring channels to be utilized in further aircraft’s service

Transversional errors in measuring aircraft parameters of motion and capabilities to correct them

W referacie przedstawiono wyniki przeprowadzonych w Instytucie Technicznym Wojsk Lotniczych (ITWL) analiz wpływu oddziaływań skrośnych na błędy pomiaru parametrów ruchu statku powietrznego przez klasyczne (elektromechaniczne) czujniki prędkości kątowej i przyspieszeniomierze liniowe. Podano zależności i przebiegi ruchu stożkowego, wytwarzanego na modelu stanowiska SRS-1 zbudowanego w ITWL. Dla posiadanych czujników prędkości kątowej I-1426 (firmy SFIM) i czujników przyspieszeń liniowych MP-95 (ZSRR) przedstawiono modele błędów skrośnych oraz podano metody ich korekcji na podstawie sygnałów z tych czujników. Dla ruchu stożkowego zobrazowano pomiary błędów skrośnych i efektywność ich korekcji przy zastosowaniu wybranych algorytmów opracowanych w ITWL.The intended aim of the paper is to present results of analyses carried out at ITWL on effects of transversional interactions that affect measuring errors of aircraft motion parameters by means of traditional (electromechanical) angular-rate sensors and linear accelerometers. Given are relationships and the course of conic motion generated on the model of the SRS-1 stand, built at ITWL. For angular-rate sensors I-1426 (SFIM) and linear-acceleration sensors MP-95 (USSR), models of transversional errors have been presented. Methods of correction based on signals emitted by these sensors have been given. For the conic motion, measurements of transversional errors and effectiveness of correction thereof using some selected algorithms developed at ITWL have been shown

Selected characteristics of the electric propulsion system of aircraft as found out from the ground-based laboratory tests

The paper is a discussion on ground-based laboratory tests of the aircraft’s electric propulsion system. The tests were intended to find relationships between environmental conditions and characteristics of the aircraft electric motor. The object under examination was a brushless DC motor AXI 2820/14 of 360 W power. Presented and discussed is the AFIT-made test bench that enables suitable, pre-planned experiments to be carried out. Discussed are also procedures of taking measurements of electric motor characteristics, followed with discussion of results. Presented selected issues of parametric description of gained results. With measurements as the basis, the relationships, first, between the electric motor’s efficiency and temperature, and second, between both the applied power and the power output (effective power) and the ambient temperature have been found. The most important findings of the testing work are, first, that the pressure does not affect the characteristics of the electric motor’s performance and second, determination of how temperature affects these characteristics. The results gained have formed the basis for the most vital flight parameters of electrically driven aircraft to be found, including the energy consumption essential for the flight range and endurance. All these findings give grounds for standardization calculations that consist in recalculation of characteristics determined in the course of aircraft flight-testing. Because of their representativeness, they also prove good illustrative examples to demonstrate properties of aircraft’s electric propulsion system

Crash tests of the protective unit of S2-3a flight data recorder

W artykule został opisany etapowy przebieg badań zjawiska zderzenia z przeszkodą sondy pomiarowej imitującej kasetę ochronną systemu rejestracji parametrów lotu S2-3a. Celem badań było uzyskanie wymaganego impulsu trapezoidalnego przeciążenia, o wartości 3400 g, działającego na kasetę przez co najmniej 3 ms dla ustalenia zgodności z normą NO-16-A200:2006 oraz EuroCAE ED-112.In the paper methodology of a crash test execution is described. The procedure was developed in a course of repeated experimental probe impact tests with changed configurations and parameters. The probe contained imitator of a crash flight data recorder S2-3a. The purpose of the studies was to obtain an test impulse envelope of trapezoidal shape of the amplitude 3400 g for et least 3 ms that comply with standards NO-16-A200:2006 and EuroCAE ED-112

Experimental determination of crash test parameters for black box data recorder

W artykule omówiony został proces określenia parametrów charakteryzujących zderzenie rejestratora katastroficznego z przeszkodą w celu ustalenia zgodności z normą NO-16-A200:2006 i ED-112. Ocenie podlega odporność rejestratora katastroficznego na przeciążenie o wartości 3400 g. Badania zrealizowano z wykorzystaniem działa pneumatycznego DPZ-250.The problem of crash tests for the black box data recorder has been discussed. By performing a sequence of experimental studies parameters of a test have been adjusted and optimized. The test meets requirements of the norm NO-16- A200:2006 and ED-112. The studies were carried out using pneumatic canon DPZ-250. The tests proved resistance of the investigated data recorder to the average overload of 3400g for 3ms