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 "micro aerial vehicles" wg kryterium: Temat

  Lista filtrów
Wyrównaj
    Wyświetlanie 1-4 z 4
    Tytuł:
    Experimental studies of leading edge vortex control of delta wing micro aerial vehicle
    Autorzy:
    Sibilski, K.
    Żyluk, A.
    Wróblewski, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/246620.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    MIcro Aerial Vehicles
    unconventional control effectors
    Opis:
    It is known, that small disturbances generated by the micro actuators can alter large-scale vortex structures, and consequently, generate appreciable aerodynamic moments along all three axes for flight control. In the current study, we explored the possibility of independently controlling these moments. We perform analytical simulations showing optimal position of LEX generators, and water tunnel measurements showing effectiveness of MEX generators as MAV control devices. We applied array of actuators located on either the forward or the rear half section of the leading edge. Both one- and two-sided control configurations have also been investigated. Experimental results showed that asymmetric vortex pairs were formed, which leads to the generation of significant torques in all three axes. The article presents typical vortical flow over a delta wing, water tunnel at Wroclaw University of Technology, experimental setup and procedures, static test results on water tunnel testing including normal forces, pitching and yawing moments, maximum values of rolling, pitching, and yawing moment coefficients, effectiveness of pitching and yawing control.
    Źródło:
    Journal of KONES; 2018, 25, 3; 393-402
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Review on delta wing against other wing designs for micro aerial vehicles
    Autorzy:
    Arun, M. P.
    Satheesh, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/2050259.pdf
    Data publikacji:
    2020
    Wydawca:
    Polska Akademia Nauk. Instytut Badań Systemowych PAN
    Tematy:
    micro aerial vehicles
    wing
    delta wing
    materials
    parameters
    survey
    Opis:
    Wings play a vital role in the design of micro aerial vehicles (MAV), in view of aerodynamic performance, maneuverability and hovering capabilities of the vehicles. The wings are generally classified as flapping, delta, swept, and so on. In this paper, the literature is reviewed regarding the diverse techniques utilized for the design, experimentation, analysis, simulation, and modeling of different types of wings. Among these types, this paper focuses on the design of delta wings. Accordingly, we review 60 relevant research papers and provide an analysis, based on their content. First, the paper presents the chronological review of the contributions relevant for the design of different types of wings. Subsequently, we focus on various materials such as stainless steel, aluminum, carbon fiber, etc., and on parameters such as Reynolds number, angle of attack, aspect ratio, etc., which are utilized for the design of wings. The paper also provides a detailed performance study regarding the contribution to the design of delta wing. Finally, we present various research issues, which can be useful for the researchers in accomplishing further research on the design of delta wings.
    Źródło:
    Control and Cybernetics; 2020, 49, 4; 525-553
    0324-8569
    Pojawia się w:
    Control and Cybernetics
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Experimental analysis of aerodynamic performance of flapping wings nano aerial vehicles
    Autorzy:
    Czekałowski, P.
    Drewniak, T.
    Sibilski, K.
    Żyluk, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/243431.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aerodynamic performance
    flapping wings micro aerial vehicles
    water tunnel measurements
    Opis:
    The aerodynamics of flapping wings is ultimately concerned with the relation between motion kinematics and the time-history of aerodynamic forces and moments. However, an important intermediate quantity is the evolution of the flow field – and in particular of flow separation. Nature’s solution to large time-varying pressure gradients, for example those due to aggressive motions, is to form and eventually to shed vortices. We are interested in understanding and exploiting these vortices – for example, in delaying vortex shedding to promote lift in situations where flow separation is in any case inevitable. From the engineering viewpoint, the question is to what extent closedform models and conventional numerical/analytical tools can estimate the aerodynamic force history, with an eye to eventually running large parameter studies and optimizations. Our paper contains results of water tunnel experiments on flapping wings aeromechanics. The idea of investigation is to optimize the wing trajectories, and to find methods providing stability and control. In the paper, we present, also, conception and methodology of tests. The investigation is dividing into two parts: preliminary and principal tests. The aim of initial part is to extract quasi – state characteristic for wings of different platforms shapes. This characteristic will be used to generate initial kinematics of movement of wing. It will be initial point of further tests. The purpose of the main experiment is to find the best way of movement for wing taking account all of unsteady phenomena (interaction between vortices, wing – wing interference, etc.). Finally, we want to identify efficient way of controlling nano-microelectromechanical flying insect (entomopter).
    Źródło:
    Journal of KONES; 2014, 21, 3; 47-57
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of micro-electromechanical inertial measurement units for unmanned aerial vehicle applications
    Autorzy:
    Mammadov, Aftandil
    Powiązania:
    https://bibliotekanauki.pl/articles/2203076.pdf
    Data publikacji:
    2022
    Wydawca:
    Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
    Tematy:
    unmanned aerial vehicles
    inertial measurement unit
    gyroscope
    accelerometer
    micro electro-mechanical system
    roll
    pitch
    yaw
    acceleration
    bezzałogowe pojazdy powietrzne
    inercyjna jednostka pomiarowa
    żyroskop
    przyspieszeniomierz
    system mikro-elektromechaniczny
    rolka
    nachylenie
    przyśpieszenie
    Opis:
    Typically, an inertial navigation system (INS) is used to determine the position, speed, and orientation of an object moving relative to the earth's surface. The navigation information (position, speed and orientation) of an unmanned aerial vehicle (UAV) is needed to control its flight. Since the resistance of INS to interferences is very high, it is possible to ensure reliable flights in conditions of high-intensity noise. This article explores the principles of constructing inertial measurement units (IMU) that are part of the INS and indicates perspective directions for their development. Micro-electromechanical inertial measurement units were studied in this work, and functional and principal electrical circuits for connecting units of inertial measurements to the microcontroller were developed. The results of practical measurements of units without calibration and after calibration were obtained using the created laboratory device. Based on the obtained results, the necessity of sensor calibration was revealed, and accuracy was improved by performing calibration with the Kalman filter algorithm. The Kalman filter is the heart of the navigation system. In a low-cost system, IMU errors like bias, scale factor error and random walk noise dominate the INS error growth.
    Źródło:
    Zeszyty Naukowe. Transport / Politechnika Śląska; 2022, 117; 129--138
    0209-3324
    2450-1549
    Pojawia się w:
    Zeszyty Naukowe. Transport / Politechnika Śląska
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-4 z 4

      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