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    Wyświetlanie 1-4 z 4
    Tytuł:
    Enhancement of Aerodynamic Efficiency of Aerofoil Using Improved Blowing and Suction System
    Autorzy:
    Balaji, K.
    Wessley, G. Jims John
    Powiązania:
    https://bibliotekanauki.pl/articles/2024000.pdf
    Data publikacji:
    2021
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    Co flow jet
    Improved blowing and suction system
    aerodynamic efficiency
    stalling angle
    control surfaces
    secondary flow
    Opis:
    Improved Blowing and Suction System (IBSS) is a novel concept that can be effectively implemented in future aircraft to improve the aerodynamic performance of aircraft wings. The proposed IBSS consists of a regular wing without its secondary control surfaces and with a Pump. The injection and suction system is used to create additional flow without disturbing the main flow over the aerofoil which effectively delays the boundary layer separation. The injection and suction areas are kept constant and they are located just below the maximum thickness point and suction is created close to the trailing edge. This paper presents a detailed numerical analysis of the proposed IBSS and the study shows that the stalling angle of attack is increased by 60% while the coefficient of lift is increased 37.5% compared to the baseline aerofoil. Also, the commercially used coflow jet (CFJ) method stalls at a 12° angle of attack whereas with the proposed IBSS method the stall occurs at a 16° angle of attack. The stalling angle is thus delayed by 33%, thus increasing the aerodynamic performance of the wing as compared to the existing methods. Also, any malfunction in IBSS does not significantly affect the performance of the aircraft. The implementation of IBSS will lead to a reduction in the weight of the aircraft and the elimination of secondary control surfaces.
    Źródło:
    Advances in Science and Technology. Research Journal; 2021, 15, 2; 116-126
    2299-8624
    Pojawia się w:
    Advances in Science and Technology. Research Journal
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analiza drgań drogowych barier akustycznych z wykorzystaniem oprogramowania Test.Lab firmy LMS
    Analysis of acoustic road barriers vibrations with the use of LMS Test.Lab software
    Autorzy:
    Bartmański, C.
    Bochenek, W.
    Dudzińska, M.
    Kompała, J.
    Martyka, J.
    Miterska, M.
    Motyka, Z.
    Passia, H.
    Ramowski, A.
    Saternus, A.
    Staniek, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/155508.pdf
    Data publikacji:
    2014
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    dopplerowska wibrometria laserowa
    ekran drogowy akustyczny
    powierzchnie drgające
    emisja fali akustycznej
    kontrola hałasu
    laser Doppler vibrometry
    acoustic road barrier
    vibrating surfaces
    sound wave emission
    noise control
    Opis:
    W artykule przedstawiono wyniki badań akustycznych barier drogowych, uzyskane z wykorzystaniem laserowego wibrometru dopplerowskiego i przetworzone z wykorzystaniem oprogramowania LMS, na przykładzie ekranu akustycznego zlokalizowanego przy drodze S1 na terenie Sosnowca. Eksperymentalną analizę modalną realizowano w środowisku Test.Lab, firmy LMS.
    In the paper, the results of tests and calculations are presented for acoustic road barrier treated as a plane vibrating surface source emitting acoustic waves. The tests were realized with the use of scanning Laser Doppler Vibrometer (LDV) which enables remote registration and the spectral analysis of vibrations for the points of the square lattice chosen on the tested surface. For comparison obtained data were also analyzed with the LMS Test.Lab software for modal analysis ([1, 2, 3, 9]). The acoustic barrier at S1 road in Sosnowiec was chosen for the in situ tests (Fig. 1). The general view of tested acoustic road barrier spot and measurement configuration is presented in the Figs 2 – 6. For the first time, the comparison was made of data analysis results obtained for acoustic barrier vibrations identified with the use of laser vibrometer PSV-400 internal tools and the ones calculated with the use of LMS Test.Lab software. The results were presented in Tab. 1, Fig. 7 and Fig. 11. In Tab. 2, Tab. 3, Tab.4 and Figs. 8 – 10, MAC coefficients (Modal Assurance Criterion, [4, 5, 6]) and identi-fied vibration modes were presented. The final method being still developed may find use in wide range of applications, e.g. for sound transmission analysis ([7], [8]) of plane acoustic road barriers for different vibration modes.
    Źródło:
    Pomiary Automatyka Kontrola; 2014, R. 60, nr 12, 12; 1100-1103
    0032-4140
    Pojawia się w:
    Pomiary Automatyka Kontrola
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Automatyczny trymer steru kierunku, rozwiązanie zwiększające bezpieczeństwo pracy pilota
    Rudder trimmer automatic solution for greater safety pilot jobs
    Autorzy:
    Cwojdziński, L.
    Powiązania:
    https://bibliotekanauki.pl/articles/312934.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Naukowo-Wydawniczy "SPATIUM"
    Tematy:
    samolot
    powierzchnie sterowe
    automatyczny trymer steru kierunku
    ATSK
    aircraft
    flight control surfaces
    Automatic Rudder Trimming System
    ARTS
    Opis:
    W artykule omówiony został systemu sterowania automatycznego trymera steru kierunku samolotu PZL 130 Orlik.
    Paper discussed information about Automatic Rudder Trimming System which is part of the PZL 130 Orlik airplane control system. Despite many advantages of turboprop engine aircraft compared with jet aircraft, piloting them has a number of different features due to P - effect. The result of this occurrence is the asymmetric deportment of the aircraft related to the symmetry surface of the plane, which both reveal during the maneuvers, as well as in a fixed flight with power changes with which the engine works. In the course of the modernization of the aircraft Orlik, the decision was taken to execute and build the aircraft PZL-130 TC II automatic trimmer rudder, causing the improvement of directional steering, and thus the safety of flights. Developing a solution is aimed at offsetting the moment gyroscope from the propeller of the aircraft and liken configuration characteristics of one turboprop engine aircraft to one jet engine. The Automatic Rudder Trimming System (ARTS) allows to broaden the use of Orlik for training in the implementation of the flights in different task systems, which significantly improve the comfort remote control navigation flights and consequently, the safety of flight operations. ARTS can be developed to the low costs autopilot, giving the ability to control the plane with coordinated trimmer expenses. Research and tests which were conducted so by the Aviation Institute in Warsaw and PZL "Warsaw" shows that such a technical solution can be applied in training aircraft PZL-130 Orlik MPT.
    Źródło:
    Autobusy : technika, eksploatacja, systemy transportowe; 2017, 18, 6; 580-583, CD
    1509-5878
    2450-7725
    Pojawia się w:
    Autobusy : technika, eksploatacja, systemy transportowe
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    System identification and heuristic control of segmented ailerons for enhanced stability of fixed wing UAVS
    Autorzy:
    Sattar, Abdul
    Wang, Liuping
    Mohamed, Abdulghani
    Fisher, Alex
    Powiązania:
    https://bibliotekanauki.pl/articles/2141835.pdf
    Data publikacji:
    2021
    Wydawca:
    Sieć Badawcza Łukasiewicz - Przemysłowy Instytut Automatyki i Pomiarów
    Tematy:
    fixed-wing UAV
    PID control
    segmented control surfaces
    system identification
    Opis:
    Different from a conventional aircraft, an investigation on system identification and control design has been carried out on a small fixed‐wing unmanned aerial vehicle (UAV) with segmented ailerons. The multiple aileron setup is configured as a multi‐input and single‐output system, and each segment is modeled as a control input. Experiments are conducted in the wind tunnel to determine the frequency responses of the system and the corresponding transfer functions. Multiple PID controllers are designed and implemented in a cascaded form for each control surface. Furthermore, a heuristic switching control strategy is implemented for the aircraft where the multiple aileron segments perform as a single aileron pair in a normal flight condition and adapt to multi‐segment control when encountering severe turbulence or significant angle reference changes. Experimental results reveal that although each control surface can stabilize the aircraft, the proposed control strategy by combining the multiple actuation surfaces reduces the mean squared errors for the roll angle up to 38 percent in the highly turbulent en vironment providing superior disturbance rejection properties.
    Źródło:
    Journal of Automation Mobile Robotics and Intelligent Systems; 2021, 15, 3; 3-14
    1897-8649
    2080-2145
    Pojawia się w:
    Journal of Automation Mobile Robotics and Intelligent Systems
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-4 z 4

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