Informacja

Drogi użytkowniku, aplikacja do prawidłowego działania wymaga obsługi JavaScript. Proszę włącz obsługę JavaScript w Twojej przeglądarce.

English (EN)·Polski (PL)·Yкраїнський (UK)
Przejdź do strony domowej biblioteki Centralna Biblioteka Wojskowa Link otwiera się w nowym oknie Logo biblioteki Prolib Integro - strona głównaCentralna Biblioteka Wojskowa

Wyszukujesz frazę "aerodynamic test" wg kryterium: Temat

  Lista filtrów
Wyrównaj
    Wyświetlanie 1-7 z 7
    Tytuł:
    Automatic taxi directional control system for general aviation aircraft
    Autorzy:
    Krawczyk, M.
    Zajdel, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/246831.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    General Aviation
    taxiing
    automatic control
    mechanics of flight
    aerodynamic test
    Opis:
    The article presents a concept of an automatic directional control system for a General Aviation class aircraft during the taxiing phase. In particular, it shows the concept of the system and the control laws synthesis – mathematical model and simulation of taxiing aircraft. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge including decreased safety, performance and pilot workload. The adapted methodology follows the model based design approach in which the control system and the aircraft are mathematically modelled to allow control laws synthesis using the Adaptive Disturbance Rejection Control method. The computer simulations are carried out to analyze the control system behavior. Chosen methodology and modelling technique, especially tire-ground contact model, resulted in a taxing aircraft model that can be used for directional control law synthesis. Aerodynamic forces and moments were identified in the wind tunnel tests for the full range of the slip angle. The results can be used for the preliminary performance assessment of the ADRC method applied in the taxi directional control system. Such system has not been introduced to General Aviation yet. Therefore, the model of taxiing aircraft including aerodynamic characteristics for the full range of the slip angle and a directional control system have a big value in the process of design and implementation of the future automatic taxi systems.
    Źródło:
    Journal of KONES; 2018, 25, 3; 299-306
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Necessary wind tunnel tests conditions of proper two- and three-dimensional measurements
    Autorzy:
    Krzysiak, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/243813.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    applied aerodynamics
    test reliability
    aerodynamic measurements
    Opis:
    In this article, the conditions to be met by a two- and three dimensional wind tunnel tests in order to ensure their correctness are presented. First of all, they relate to the flow similarity between the real and wind tunnel conditions. This similarity enforces a wind tunnel calibration, a proper design and manufacturing of the tested models, a proper research, as well as processing of obtained test data including the usage of the wind tunnel corrections. In this work, the majority of these conditions were presented but in particular, the influence of the wind tunnel corrections on the tested models aerodynamic characteristics is consider. The two-dimensional airfoil studies and three-dimensional aircraft model balance investigation were performed in two low speed wind tunnels of a different sizes of theirs test section. The wind tunnel tests were performed in two Institute of Aviation low speed wind tunnels, namely in the wind tunnel T-1 (of the 1.5 m diameter test section) and in the wind tunnel T-3 (of the 5 m diameter test section), at the same undisturbed velocity, V∞ = 40 m/s. The comparison of the lift coefficient characteristic obtained in two different wind tunnels using the same two and three-dimensional models and same measurement techniques enabled to discuss the problem of necessity of the wind tunnel corrections usage.
    Źródło:
    Journal of KONES; 2018, 25, 3; 315-322
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Wind tunnel tests of the Tu-154M aircraft aerodynamic characteristics
    Autorzy:
    Krzysiak, Andrzej
    Powiązania:
    https://bibliotekanauki.pl/articles/245216.pdf
    Data publikacji:
    2019
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    applied aerodynamics
    test reliability
    aerodynamic measurements
    Opis:
    Determination of possible manoeuvres to be performed by the aircraft requires knowledge of its aerodynamic characteristics including, in particular, characteristics of the aircraft at configuration with deflected control surfaces. In this article, the wind tunnel tests results of the model of passenger Tu-154M aircraft manufactured at the scale 1:40 are presented. The model was designed and manufactured by the Military University of Technology based on the Tu154M aircraft geometry obtained by full-scale object scanning. The model mapped all aircraft control surfaces, along with the gaps between these surfaces and the main wing part. During the tests all the model’s control surface like, flaps, ailerons, spoilers, slots, rudder, elevator and tail plane were deflected at the same deflection angles range as they are used in the full scale aircraft. The aerodynamic characteristics of the tested Tu-154M aircraft model were measured by the 6-component internal balance. Based on the obtained measurements the aircraft model aerodynamic coefficients were calculated. In the article the basic aerodynamic characteristics of the tested Tu-154M aircraft model i.e. lift, drag coefficients as well as pitching, yawing and rolling moment coefficients versus model angles of attack and sideslip angles were presented. The tests were performed in the Institute of Aviation low speed wind tunnels T-1 of the 1.5 m diameter test section at the undisturbed velocity, V∞ = 40 m/s
    Źródło:
    Journal of KONES; 2019, 26, 3; 113-120
    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:
    Prediction and validation for the aerodynamic noise of high-speed train power car
    Autorzy:
    Jiang, S.
    Yang, S.
    Wu, D.
    Wen, B-Ch.
    Powiązania:
    https://bibliotekanauki.pl/articles/375504.pdf
    Data publikacji:
    2018
    Wydawca:
    Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
    Tematy:
    aerodynamic noise
    high-speed train
    Lighthill-Curle theory
    simulation model
    online test
    hałas aerodynamiczny
    pociąg ekspresowy
    teoria Lighthilla-Curle
    model symulacyjny
    test online
    Opis:
    The aerodynamic noise of high-speed train power car was investigated in this article. The full-scale power car was first modeled, and the external steady flow field was computed by a realizable k-ε turbulence model. The aerodynamic noise sources of the power car surface and the external transient flow field were then calculated by broadband noise source model and large eddy simulation (LES) model, respectively. The static pressures on the train surface were obtained from the results of the transient model. Considering the transient flow field, the far-field aerodynamic noise generated by the power car was finally derived from Lighthill-Curle theory. It was validated by means of on-line tests that have been performed along a real high-speed railway line. Through comparisons between simulations and measurements, it is shown that the simulation model gives reliable aerodynamic noise predictions. We foresee numerous applications for modeling and control of the aerodynamic noise in high-speed train.
    Źródło:
    Transport Problems; 2018, 13, 2; 91-102
    1896-0596
    2300-861X
    Pojawia się w:
    Transport Problems
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    WPŁYW OBCIĄŻEŃ OD WIATRU NA BUDYNEK WYSOKI O NIEREGULARNEJ FORMIE – BADANIA MODELOWE
    WIND LOADS’ INFLUENCE ON THE HIGH-RISE BUILDING OF AN IRREGULAR FORM – MODEL STUDIES
    Autorzy:
    Rokicki, Wiesław
    Pietrzak, Joanna
    Wrona, Mariusz
    Powiązania:
    https://bibliotekanauki.pl/articles/441530.pdf
    Data publikacji:
    2017
    Wydawca:
    Sopocka Akademia Nauk Stosowanych
    Tematy:
    skyscraper
    analyze according to Eurocode
    wind tunnel test
    aerodynamic
    shaping
    wieżowiec
    analiza normowa
    badania tunelowe
    aerodynamika
    kształtowanie
    Opis:
    W referacie nawiązano do przeprowadzonych analiz oddziaływania wiatru na wieżowiec o nieregularnym rzucie i wysokości nieprzekraczającej 200 m. Celem badawczym było porównanie przyjmowanych normowych wartości obciążeń wiatrem, w stosunku do wartości uzyskanych w badaniach modelowych. Porównanie przeprowadzono w zakresie ciśnień szczytowych wiatru działających na fasady oraz sił wypadkowych działających na konstrukcję budynku. Zasadnicze różnice wynikały z braku uwzględnienia wpływu sąsiedniej zabudowy w obliczeniach wg PN-EN. Wypadkowe siły powstałe po scałkowaniu pomierzonych doświadczalnie ciśnień były znacznie mniejsze niż siły założone zgodnie z PN EN. Można stwierdzić, że wyniki uzyskane z badań doświadczalnych, jako opracowania bardziej miarodajne, mogą stanowić podstawę do przyjmowania mniejszych wartości obciążeń.
    In the paper there is reference to the analysis of wind influence on the skyscraper of an irregular plan and the height not exceeding 200 metres. The aim of the research was the comparison of wind load values based on eurocodes in relation to the results of experimental research carried out in an aerodynamic tunnel. The comparison concerned wind spike pressure influencing the facades of the building and resultant forces acting on its structure. The major differences of force values calculated in accordance with euro codes and these obtained from experimental research resulted from not taking into account the influence of neighbouring buildings in calculations based on PN-EN. The resultant forces arising from the integration of experimentally measured pressure were significantly smaller than those calculated in accordance with PN-EN. To conclude, one might state that the results obtained from experimental research - as more reliable ones - could be the basis for assuming smaller wind loads.
    Źródło:
    Przestrzeń, Ekonomia, Społeczeństwo; 2017, 12/II; 179-191
    2299-1263
    2353-0987
    Pojawia się w:
    Przestrzeń, Ekonomia, Społeczeństwo
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    A two-point approximation approach to determining aircraft aerodynamic force coefficients for a maximal-duration horizontal flight
    Metoda dwupunktowej aproksymacji do wyznaczania współczynników sił aerodynamicznych dla lotów horyzontalnych o maksymalnym czasie trwania
    Autorzy:
    Goncharenko, Andriy Viktorovich
    Powiązania:
    https://bibliotekanauki.pl/articles/36445953.pdf
    Data publikacji:
    2021
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    aerodynamic force
    aerodynamic coefficient
    test
    trial
    aircraft
    flight
    maximal duration
    maximal distance
    horizontal flight
    siła aerodynamiczna
    współczynnik aerodynamiczny
    próba
    statek powietrzny
    maksymalny czas trwania
    maksymalny dystans
    lot
    lot horyzontalny
    Opis:
    This paper proposes a two-point approximation approach to determining aircraft aerodynamic force coefficients, and compares it to the traditional methods. A variational concept is used to conduct aircraft flight trials for the maximal duration of quasi-horizontal flights. The advantages of the described optimization theories are demonstrated, in terms of aviation fuel gas savings. The results of a numerical example are presented.
    W pracy zaproponowano metodę dwupunktowej aproksymacji do wyznaczania współczynników sił aerodynamicznych samolotu i porównano ją z metodami tradycyjnymi. Koncepcja wariacyjna jest wykorzystywana do prowadzenia prób w locie samolotu dla maksymalnego czasu trwania lotów quasi-horyzontalnych. Przedstawiono zalety opisanych teorii optymalizacyjnych w aspekcie oszczędności paliwa lotniczego. Przedstawiono wyniki przykładu numerycznego.
    Źródło:
    Transactions on Aerospace Research; 2021, 3 (264); 71-80
    0509-6669
    2545-2835
    Pojawia się w:
    Transactions on Aerospace Research
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-7 z 7

      Ta witryna wykorzystuje pliki cookies do przechowywania informacji na Twoim komputerze. Pliki cookies stosujemy w celu świadczenia usług na najwyższym poziomie, w tym w sposób dostosowany do indywidualnych potrzeb. Korzystanie z witryny bez zmiany ustawień dotyczących cookies oznacza, że będą one zamieszczane w Twoim komputerze. W każdym momencie możesz dokonać zmiany ustawień dotyczących cookies