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    Wyświetlanie 1-5 z 5
    Tytuł:
    Identification of main helicopters resonances by ground vibration test
    Autorzy:
    Wiśniowski, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/242575.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    helicopter
    resonance
    modelling
    ground vibration test
    Opis:
    Six resonances of the helicopter body standing on the airport apron and at least two resonances of the free helicopters the frequencies of which are within the range of basic loadings by the helicopter rotor is called (8+) model. It was proposed to identify (8+) model with the use of resonance tests. It was indicated that (8+) model allows for detuning the resonances from the frequency of working loads, tracing the process of moving through resonances as well as taking off and landing. The paper presents: example of a helicopter on a test rig and visible vibrations inductors; induction of resonance vibrations, induction of resonance vibrations with the forms of pitching, yawing, rolling; induction of resonance vibrations with the forms of pitching with opposite pylon yawing and tipping with opposite pylon yawing; model of helicopter resonances; the multiplication of the resonance amplitude for various velocities of moving through with visible growth of the resonance frequency and reduction of vibrations amplitude; change of the frequencies at the taking off and landing.
    Źródło:
    Journal of KONES; 2015, 22, 2; 287-291
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Innovationality is the transfer process from the idea to commercialization
    Autorzy:
    Wiśniewski, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/243893.pdf
    Data publikacji:
    2010
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    ground vibration test
    modal analysis
    aircraft structure dynamics
    Opis:
    In today's world, innovationality is synonymous with modernity, development, good governance and strategic thinking. The country 's economy and whole of society should be innovative. The research and development process and the results of the work would be reviewed from the commercialization perspective. The all innovative projects should finish on thefree market, but majority of them end their lives at the research and development stage. The idea of spin-off corporations has to serve the subordination of the entire innovative project realization cycle to the vision of its commercialization. Innovative society and economy require implementation of both large and small innovations, created in large, medium and small R & D programs. In economically leading countries, the mega-programs play an important role in innovationality. small innovation programs are usually created by small research teams and individual inventors. For the balanced development of the country's economy, there is a needfor the variety, both small and large innovation programs. In the absence of an effective opportunity to realize one's own Polish mega-programs, it is worth to consider the mega-program named: ,,Provision of services on the International research market" as a Polish specialty. For 10 years the Warsaw's Institute of Aviation pursues this strategy. The Institute of Aviation employs about 800 specialists, which perform the advanced research of the new materials and designs for the new gas turbine engines and combustion systems.
    Źródło:
    Journal of KONES; 2010, 17, 1; 485-488
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Effect of changes in some design parameters on the dynamic properties of aircraft
    Autorzy:
    Wiśniewski, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/243891.pdf
    Data publikacji:
    2010
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    ground vibration test
    modal analysis
    aircraft structure dynamics
    Opis:
    The aim of the study presented in the paper was to examine the impact of changes related to aircraft modernization, the dynamic properties of an aircraft on the basis of five cases studied experimentally. Which changes in the dynamics of an aircraft structure occurred as a result of modernization can be experimentally tested by resonance tests. For this purpose, resonance tests should be carried out before the aircraft modernization and after its completion. In order to mapping the conditions of free flight the objects were suspended flexibly. The electrodynamics actuators were used to induce vibrations, piezoelectric transducers were used for the measurement of vibrations. The size and phase of extortion forces and their application points were selected individually for each resonance in order to get the best separation of it. The first stage of the study was based on recordings the frequency - amplitude characteristics. The second stage of the study was the Identification of individual frequencies and mode shapes of each resonance, which was implemented by choosing the size and the proportion of mutual phase shifts between the extortion forces. In the selection the criteria based on minimizing the phase difference of vibrations measured at several points of the structure were used. The final stage of this study was to register the frequency and shapes mode of the tested resonance and the resonance generalized masses and damping coefficients.
    Źródło:
    Journal of KONES; 2010, 17, 1; 479-483
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Methods of modern aircraft aeroelastic analyses in the institute of aviation
    Autorzy:
    Chajec, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/247210.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    flutter
    normal modes
    ground vibration test
    unsteady aerodynamic model
    Opis:
    The aeroelastic phenomena analysis methods used in the Institute of Aviation for aircraft, excluding helicopters, are presented in the article. In industrial practice, a typical approach to those analyses is a linear approach and flutter computation in the frequency domain based on normal modes, including rigid body modes and control system modes. They are determined by means of the finite element method (FEM) model of structure or a result of ground vibration test (GVT). In the GVT case, relatively great vibration amplitudes are applied for a good examination of a not truly linear structure. Instead or apart from the measure of generalized masses, a very theoretical model is used for mode shapes cross orthogonality inspection and improvement. The computed or measured normal mode sets are the basis for flutter analysis by means of several tools and methods, like MSC.Nastran and ZONA commercial software as well as our own low-cost software named JG2 for the flutter analysis of low speed aeroplanes and for a preliminary analyses of other aircraft. The differences between the methods lie in determining normal mode set, unsteady aerodynamic model, flutter equation formulation, time of analysis, costs, etc. Examples with results comparison obtained by means of distinguished methods are presented. Some works in the field of aeroelastic analysis with nonlinear unsteady aerodynamic in the time domain using Tau-code and ANSYS Fluent software were also performed. Aeroelastic properties of deformed structures, like a sailplane with deflected wings, can be also analysed. The simplest way of this analysis is the semi-linear approach in which the deflections modify the aircraft geometry for normal modes determination.
    Źródło:
    Journal of KONES; 2018, 25, 4; 33-42
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Pomiary drgań izolowanych fragmentów konstrukcji płatowcowych z zastosowaniem analizatora modalnego LMS SCADAS Lab
    Vibration Testing of Some Isolated Fragments of Airframe Structure with the Use of Modal Analyser LMS SCADAS Lab
    Autorzy:
    Olejnik, A.
    Rogólski, R.
    Szcześniak, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/403719.pdf
    Data publikacji:
    2017
    Wydawca:
    Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
    Tematy:
    naziemne próby rezonansowe (GVT)
    analiza modalna konstrukcji
    drgania własne
    ground vibration test (GVT)
    experimental modal analysis (EMA)
    normal mode analysis
    Opis:
    Przed wydaniem świadectwa typu dla wprowadzanego do eksploatacji samolotu nadzór lotniczy w myśl obowiązujących przepisów określa wymogi dotyczące min. testów wibracyjnych. Na etapie uzyskiwania zgody na próby w locie należy wykazać brak zagrożeń konstrukcji ze strony zjawisk dynamicznych poprzez analizy i symulacje drgań oraz wykonanie naziemnych prób rezonansowych GVT (Ground Vibration Testing). W toku pomiarów typu GVT określa się krytyczne częstotliwości i postacie drgań. W niniejszym artykule opisano proces identyfikacji drgań rezonansowych izolowanego skrzydła zastrzałowego przy użyciu aparatury do pomiarów modalnych z analizatorem widma drgań LMS SCADAS Lab. Wykorzystując wskazaną aparaturę w odniesieniu do rzeczywistej konstrukcji płatowcowej, właściwie przygotowanej pod względem rozkładu masy, sztywności, swobody ruchu sterów i klap oraz warunków mocowania, można wyznaczyć kluczowe charakterystyki drganiowe odpowiadające punktom rezonansowym. Opisano tok procesu pomiarowego obejmującego takie etapy, jak: przygotowanie obiektu, konfiguracja aparatury, przygotowanie modelu symulacyjnego, orientacyjna identyfikacja punktów modalnych w trybie przemiatania zakresowego oraz dostrajanie częstotliwości rezonansowych przy różnych konfiguracjach wzbudzania. Wyniki testów doświadczalnych porównano z częstotliwościami analogicznych postaci własnych wyznaczonych dla modelu dyskretnego MES. Zademonstrowano też sposób wyznaczania postaci lokalnych w toku wymuszania drgań całego płatowca (samolot Flaris).
    Prior to the issue of a type-certificate for an airplane put into service, aeronautical surveillance, in accordance with the applicable regulations, the requirements concerning, among other things, vibration tests. At the stage of approval for flight tests, no structural hazards from dynamic phenomena shall be demonstrated by vibration analysis and simulations and ground vibration tests (GVT). In the course of GVT measurements, critical frequencies and vibration mods are defined. This article describes the process of identifying resonant vibrations of an isolated strut-braced wing using modal measurement instruments with LMS SCADAS Lab vibration spectrum analyser. Using the indicated apparatus with respect to the actual fuselage structure, properly prepared in terms of mass distribution, stiffness, freedom of movement of the rudder and flap and mounting conditions, key vibration characteristics corresponding to the resonance points can be determined. The process of measuring process has been described including the preparation of the object, the configuration of the apparatus, the preparation of the simulation model, the indicative identification of the modal points in the sweeping mode and the tuning of the resonant frequencies with different excitation configurations. The results of the experimental tests were compared with the frequencies of analogous self-defined characters for the discrete MES model. Also demonstrated is the way of locating the local characters in the course of enforcing the vibration of the entire airplane (Flaris aircraft).
    Źródło:
    Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa; 2017, 8, 3 (29); 127-144
    2081-5891
    Pojawia się w:
    Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-5 z 5

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