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    Wyświetlanie 1-13 z 13
    Tytuł:
    Non-destructive evaluation of rescue and patrol unmanned aerial vehicle
    Autorzy:
    Pawluczy-Majka, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/243854.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    NDT diagnostics
    active thermography
    Opis:
    With the growing intensity of civil usage of the UAV, one of the most important problems is safety. It consists of operational safe use of the UAV in the common air area and reliability of the aerial vehicle construction. Each flying object is subjected to external loads, which influence on it in flight and on the ground. The external loads are mainly caused by aerodynamic, weight and inertia influence, ground reaction force and the power unit [1]. That is why during service, UAV structures are prone to many mechanical and environmental conditions that can damage to composite structures in the form of delamination, fiber breakage, and matrix cracking. Monitoring the level and type of damage to a composite structure is vital to determining the component’s structural integrity and preventing the failure of the structure during flight [2]. Non-destructive testing which has been used so far to identify defects in the aircraft structure made from metallic materials has a quite limited application in the case of composite structures. With the growing use of composites in the aviation industry, a necessity appears to work out a method allowing identification of technological defects and damages appeared in the process of the UAV’s operation. The answer to the appearing demand could be, for instance, the active thermography technique used for the thin wall test of the skin elements of the UAV. The obtained research results bring closer the problem of selection of the quick, well-fitted non-destructive testing method depending on the kind of the diagnosed construction.
    Źródło:
    Journal of KONES; 2014, 21, 4; 411-416
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    An analysis of phugoid oscillations of unmanned flying wing
    Autorzy:
    Mioduska, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/242816.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    flying wing
    longitudinal stability
    phugoid oscillations
    Opis:
    The flying wing configuration has been considered by airplane designers for more than one hundred years. Tailless aircraft have been inspired by nature and its solutions. In present times, this configuration is used to design Unmanned Aerial Vehicle (UAV). This type of plane could serve personal, military and research purposes. The flying wing is characterized by large amount of payload space, smaller wetted area than conventional airplane and stealth capability. This makes, that it is widely applicable in rescue operations, geodetic and cartographic research, monitoring of natural resources, taking pictures or videos. Despite all the merits of tailless plane, it also has its downsides. The main problem of this type of aircraft is longitudinal stability. A conventional airplane can compensate the pitch moment of the wing with its horizontal tail but a flying wing is tailless. A slow decay of oscillations amplitude is the problem, which can be solved by active control or proper aerodynamic design. A combination of geometric characteristic such as sweep, taper, twist and location of vertical stabilizers along span, can lead to stable flying wing. In this article, the results of phugoid oscillations analysis of unmanned flying wing are presented. Research platform was X8-2, popular flying wing UAV, designed for First Person View (FPV) method to control the vehicle. The calculations were performed using 3D panel method. On the basis of calculations for three versions of the model aircraft, the dynamic characteristics were created. The analysis of longitudinal stability undertaken here has indicated propriety of applied changes in geometry.
    Źródło:
    Journal of KONES; 2016, 23, 2; 247-254
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Problems of control of mini unmanned aerial vehicle (MINIUAV)
    Autorzy:
    Hajduk, J.
    Homziuk, A.
    Kuliński, M.
    Sabak, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/242360.pdf
    Data publikacji:
    2009
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    technical object
    engineering
    miniature avionics system
    Opis:
    It was introduced suggestions and results concerning some of control miniUAV problems in this article. They were formulated on base of theoretical and experimental investigations. Now the own construction miniature system avionics is being investigated. This system is designed to stabilisation of miniUAV and to control of navigation with GPS signal. Now system is used also as flight control recorder. The avionics control system which lets for very good and saved navigation miniUAV should be created. more over this system should use GPS signal and miniature sensors. Especially, a block Junction diagram of a miniature avionics unit - miniBSP MSOP. = 3 accelerometers, 3 rate gyroscopes, static pressure sensor, dynamic pressure sensor, control path in the autopilot channel of pitch and roll during the Start and Steady Flight stage, Control path in the draught control channel during Start and Steady Flight stage, general scheme of a ground-based flight control to pilot miniBSP unmanned aircrafts, visualization of the ground-based flight control station operation, airframe for testing during flight, positions of equipment items in the miniBSP airframe are presented in the paper.
    Źródło:
    Journal of KONES; 2009, 16, 2; 167-173
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Use of 3D printing technology in the aviation industry on an example of numerical experimental stress state analysis of unmanned aerial vehicle wing
    Autorzy:
    Święch, Ł.
    Bendarz, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/246287.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    DIC
    3d printing
    FFF
    stress state
    UAV
    Opis:
    The article presents the results of static tests performed on the primary support structures of a TWISST-ter unmanned aircraft constructed using additive manufacturing techniques commonly known as 3D printing. The primary goal of the experiment was determining the material effort of the structure in order to assess the feasibility of such an engineering solution in terms of material mechanics. Considering the fact that the properties of 3D printed elements are not widely known, both destructive experimental methods and finite element methods were used. During the experimental trails, the ARAMIS deformation measurement system, based on digital three-dimensional image correlation, was used. The results of this experiment allowed for the calibration of the numerical model as achieving convergence with experimentally determined strain fields. This approach ensured the correctness of the numerical determined stress state. Based on the results of the study, the necessary design improvements were implemented and a general conclusion was formed regarding of the numerical analysis of structures made through 3D printing.
    Źródło:
    Journal of KONES; 2017, 24, 4; 327-334
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Use of construction materials in unmanned aerial vehicles
    Autorzy:
    Adamski, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/245052.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    Unmanned Aerial Vehicle
    UAV
    construction materials
    material properties
    Opis:
    The design process is mostly connected with a proper selection of construction materials. Newly designed UAVs must undergo assessment in terms of performed tasks, range or fuel consumption. A significant influence upon the selection of materials, which are long lasting and resistant to damage, is exerted by the conditions of work of Unmanned Aerial Vehicles. They mainly execute their tasks at high altitudes with high speeds, where temperature and pressure differences may extensively damage not only the airframe skin, but also the equipment and the propulsion system itself. The aim of this study is to present the characteristics of materials currently used as well as their assessment in employed construction elements of UAVs. Polymer composites are superior to Al and Ti alloys, steel within the parameters of tensile strength and stiffness. As for the density gradient, polymer carbon fibre composites exceed glass fibre composites, also under cyclically variable loads. Glass fibre composites during tensile testing show higher values and a higher capability of absorbing energy under static and dynamic forces. Polymer matrix composites, reinforced with Kevlar, are less stiff than carbon-fibre composites, due to lower values of elasticity modulus, however they demonstrate higher impact load. Strength tests provide valuable data concerning the properties of a given material, such as tensile modulus E [MPa], tensile strength UTS [MPa], or resistance to high temperatures. It must be noted that these properties significantly affect the functioning of the airframe and its components.
    Źródło:
    Journal of KONES; 2016, 23, 3; 11-17
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Concept of tiltrotor UAV control system
    Autorzy:
    Ciopcia, M.
    Szczepański, C.
    Powiązania:
    https://bibliotekanauki.pl/articles/247022.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    tiltrotor
    control system
    rotor przechyłu
    system sterowania
    Opis:
    Nowadays, civil UAV industry market grows rapidly. This expansion is followed by the new requirements and expectations against UAVs, which force their constructors to look for less typical solutions. Expected long time endurance and range are the typical examples of such expectations. Clients are often looking for UAV with VTOL ability and time of flight much greater than 30 minutes and long range. They want to inspect large areas, i.e. between major cities without need of paying for building and maintaining developed aircraft infrastructure. Example of UAV with low infrastructure requirements are multirotors. Major disadvantage of them is short flight time. Elongating time of flight is hard to achieve by classical multirotor with standard Li-Pol batteries available on the market. They have too low energy density in currently used technology. Alternative power solutions, like fuel cells, have low financially rewarding factor, which cause whole projects to be unprofitable. Foregoing circumstances force engineers to find less usual ways for improvement energy efficiency, which will cause extending the time and range of flight. One of them is a tiltrotor. Tiltrotors are hybrid solutions – they combine airplane and multirotor capabilities to achieve features, which exclude each other in classical constructions. Aircraft-like wing make it able to use its lift-to-drag ratio to achieve energy savings, higher top speed and extended range in comparison with multirotors. UAV is also equipped with multiple multirotor-style engines with additional capability to rotate itself in pitch. In horizontal engine position, vehicle behaves like classical multirotor – allowing pilot to hover and perform VTOL manoeuvres. When engines are tilted to vertical position, whole UAV get performance similar to airplane – high speed and flight endurance. In the other hand, practical implementation of tiltrotor solution can be problematic: simulation, steering and controlling such aircraft in transition state are complex tasks. Moreover, designed aircraft should follow major rule connected with multirotors: Should have as simple, robust mechanical design as it can. Proposed article will concentrate on concept and preliminary design of fly-by-wire steering system with unique properties for tiltrotor. One of such properties will be unification of steering method – which eliminates need for switch and setting initial conditions for control subsystems, when flight procedure requires changing flight mode. Second important improvement will be possibility to use transitional states as intermediate state between propeller driven fly and gliding – which allow achieving wide spectrum of flight speeds. Moreover, huge number degrees of freedom (at least 9) create new opportunities for steering optimization. Extensive thrust vectoring abilities of such UAV could not only implicate substantial efficiency improvement of multirotors, but also improve its manoeuvrability. The article will focus on basic concepts of kinematics, steering of such UAV and show proposition of energyusage oriented optimization for its control trajectories. To let mechanical design be simple, all control and steering methods will be implemented in software, which will implicate complex structure of steering system. Overcoming complexity of software should be profitable in relation to expected improvements of UAV capabilities.
    Źródło:
    Journal of KONES; 2017, 24, 1; 83-89
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Optimisation of aircraft position in the formation flight for the drag reduction
    Autorzy:
    Antczak, A.
    Sibilski, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/245259.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    formation flying
    optimisation
    dynamic of flight
    aerodynamic
    Opis:
    This article presents optimisation of necessary flight thrust in a V-shaped flight formation of small-unmanned plane “Sikorka”. At the beginning is showed analyse of birds behaviour. Their formation flying was the cause of attention in order to minimalize fuel consumption. Afterwards there are overlooked scientific articles about the formation flying subject contain pure physic analyses, and articles about researches which was made in order to explain economic beneficial for airlines. Thus, the article presents mathematical model, which was optimised for three different starting position of a longitudinal axis. After optimisation there are presented results of the wingman position in regard of the leader. Influence of the calculation results on the formation flying was analysed, allowing for some conclusions about the future of the UAV’s flights. The given process is aimed to achieve the best (optimal) solution from the point of view of the specific criterion. The following most important terms can be distinguished within the optimization process: decisive variables – parameters determining the basic project assumptions. The basic design variables and design constrains are described.
    Źródło:
    Journal of KONES; 2018, 25, 3; 39-50
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Initial state evaluation algorithm using fuzzy Bellman method
    Autorzy:
    Gruszecki, J.
    Basmadji, F. L.
    Powiązania:
    https://bibliotekanauki.pl/articles/243933.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    guidance
    trajectory
    mountainous terrain
    poradnictwo
    trajektoria
    teren górski
    Opis:
    The problem of UAV control along a predefined trajectory is a well know problem and there are several methods that could accomplish this task. However, adding final conditions that the UAV have to meet at the end of the trajectory makes this problem more difficult. In this article, the authors present a fuzzy based method that is not time consuming and can solve this problem. The algorithm for flying at low altitudes are aimed to ensure the maximum safety of the flight by considering only the acceleration values that are possible to achieve by the object. In particular, the article presents: flight trajectory over mountainous terrain, the structure of altitude control system, the structure of normal acceleration control system, exemplary calculations and an object with velocity equals, membership functions of angle of attack, solutions' illustration, flight path angle and pitch angle along the trajectory, the demanded and actual normal acceleration along the trajectory and flying object trajectory.
    Źródło:
    Journal of KONES; 2017, 24, 1; 159-169
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Algorithms for detecting disorders of the BLDC motor with direct control
    Autorzy:
    Chodnicki, M.
    Kordowski, P.
    Nowakowski, M.
    Kowaleczko, G.
    Powiązania:
    https://bibliotekanauki.pl/articles/246323.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    Unmanned aerial vehicle
    video stream
    BLDC motor
    rotation matrix
    Opis:
    Unmanned aerial vehicles are used to observe objects from the air in both kind of users – military and civilian. During the flight, UAV constantly is changing its orientation. This is due to weather conditions and commands coming from the ground control station. It has directly influence to the quality of the video stream transmitted from the cameras to the GCS. That disturbed image is hard to effective analyse. In order to eliminate the interference, UAVs are equipped with stabilized gimbals. The most of gimbals designed in Air Force Institute of Technology are using BLDC motors. Some of these systems use encoders for determining the absolute angle of motor rotation. The smaller one, which is up to 200 g, is not provided with these sensors. This angle is calculated without any feedback from the system. It is calculated by the BLDC motor`s control signals. However, lack of feedback can provide unstable work of gimbal, if it will be pushed by any force from environment. During the flight, it is unacceptable to head optoelectronic stopped working steadily. Therefore, there is a need to develop algorithms for securing the proper operation of the system stability. These algorithms can be used in other systems using stepper or BLDC motors.
    Źródło:
    Journal of KONES; 2016, 23, 4; 49-54
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Quadrotor UAV control for transportation of cable suspended payload
    Autorzy:
    Kusznir, Tom
    Smoczek, Jarosław
    Powiązania:
    https://bibliotekanauki.pl/articles/246855.pdf
    Data publikacji:
    2019
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    transport
    UAV
    quadrotor
    under actuated
    cable suspended payload
    sliding mode control
    Opis:
    Payload transportation with UAV’s (Unmanned Aerial Vehicles) has become a topic of interest in research with possibilities for a wide range of applications such as transporting emergency equipment to otherwise inaccessible areas. In general, the problem of transporting cable suspended loads lies in the under actuation, which causes oscillations during horizontal transport of the payload. Excessive oscillations increase both the time required to accurately position the payload and may be detrimental to the objects in the workspace or the payload itself. In this article, we present a method to control a quadrotor with a cable suspended payload. While the quadrotor itself is a nonlinear system, the problem of payload transportation with a quadrotor adds additional complexities due to both input coupling and additional under actuation of the system. For simplicity, we fix the quadrotor to a planar motion, giving it a total of 4 degrees of freedom. The quadrotor with the cable suspended payload is modelled using the Euler-Lagrange equations of motion and then partitioned into translation and attitude dynamics. The design methodology is based on simplifying the system by using a variable transformation to decouple the inputs, after which sliding mode control is used for the translational and pendulum dynamics while a feedback linearizing controller is used for the rotational dynamics of the quadrotor. The sliding mode parameters are chosen so stability is guaranteed within a certain region of attraction. Lastly, the results of the numerical simulations created in MATLAB/Simulink are presented to verify the effectiveness of the proposed control strategy.
    Źródło:
    Journal of KONES; 2019, 26, 2; 77-84
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Ocena stanu technicznego nawierzchni drogi startowej lotniska przy użyciu bezzałogowego statku powietrznego
    Assessment of the technical condition of the airport runway surface using an UAV
    Autorzy:
    Żebrowski, Marcin
    Powiązania:
    https://bibliotekanauki.pl/articles/38926581.pdf
    Data publikacji:
    2023
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    BSP
    UAS
    NMT
    GRID
    niweleta
    GPS RTK
    nawierzchnia lotniskowa
    UAV
    gradeline
    airport pavement
    Opis:
    Stan techniczny nawierzchni lotniskowych ma istotny wpływ na wykonywanie operacji powietrznych w polu naziemnego ruchu lotniczego, a także wpływa na komfort poruszania się statków powietrznych po nawierzchni lotniskowej, co stanowi o bezpieczeństwie wykonywanych operacji lotniczych. Wymagania w zakresie nawierzchni lotniskowych, określone są w normach obronnych, a także w dokumentach cywilnych, np. ICAO (International Civil Aviation Organization), EASA (European Union Aviation Safety Agency), FAA (Federal Aviation Administration), gdzie określono parametry eksploatacyjne w zakresie konstrukcji nawierzchni lotniskowych. W artykule przedstawiono metodykę wstępnej oceny stanu technicznego nawierzchni lotniskowych w zakresie występujących uszkodzeń, a także anomalii istniejącej niwelety, mogącej świadczyć o nieodpowiedniej równości nawierzchni. Ocenę wykonano przy użyciu zestawu do fotogrametrii lotniczej oraz przedstawiono wyniki badań. Skoncentrowano się na wykorzystaniu zestawu do fotogrametrii lotniczej, który wykonał nalot nad drogą startową lotniska wojskowego oraz wykonał jej pełne zobrazowanie.
    The technical condition of airport pavements not only has a significant impact on the performance of air operations in the ground movement area but also affects the comfort of aircraft movement on the airport pavement, which determines the safety of air operations. The requirements for airfield pavements are specified in defense standards, as well as in civil documents, e.g. (International Civil Aviation Organization), EASA (European Union Aviation Safety Agency), FAA (Federal Aviation Administration), where exploitation parameters in the field of airport pavement construction are defined. The article presents the methodology of the initial assessment of the technical condition of airport pavements in terms of existing damage, as well as anomalies of the existing gradeline, which may indicate inadequate evenness of the pavement. The assessment was made using an aerial photogrammetry kit and the test results were presented. This work focuses on the use of an aerial photogrammetry set, which made a flight over the runway of a military airport providing its full imaging.
    Źródło:
    Journal of KONBiN; 2023, 53, 3; 15-28
    1895-8281
    2083-4608
    Pojawia się w:
    Journal of KONBiN
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis and conceptual design of micro class UAV for aerodesign international competition
    Autorzy:
    Figur, K.
    Lorenc, W.
    Nykaza, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/242812.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    UAV
    unmanned aerial vehicle
    drone
    analysis
    aircraft design
    bezzałogowy statek powietrzny
    dron
    analiza
    projekt samolotu
    Opis:
    Aero Design is an annual student competition held by Society of Automotive Engineers in which the goal is to design and build a flying UAV capable of lifting the highest payload while observing lowest payload weight and fitting in a specified carrying case. To achieve that task teams have to choose between conflicting objectives that are lowest empty weight and highest lifting capacity. The rules state that design to enter the competition must be a fixed wing aircraft fitting in a box with inside dimensions of 24x18x8 inches. The payload bay has to be a rectangular block measuring 5x2x2 inches. There also is a limit of 55 pounds total weight with payload. The aircraft must take of either by hand launch or be propelled using a rubber tubing, than do a 360-degree circuit of the flying field and finally land within 200 feet landing zone. The article presents requirements analysis, weather research, design research, considered about launch method, wing layout and aircraft layout study (napkin sketches).
    Źródło:
    Journal of KONES; 2017, 24, 1; 129-135
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Application of drones in protection of state border
    Autorzy:
    Adamski, M.
    Mieżaniec, J.
    Adamski, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/242649.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    Unmanned Aerial Vehicles
    flying platform
    drone
    unmanned
    UAV
    Unmanned Aerial Vehicle
    fly eye
    Border Guard
    operator
    Opis:
    An unmanned aerial vehicle is a flying apparatus that does not require a crewmember on board to complete a task. Its piloting is done by means of indirect control. UAVs also have the ability to perform autonomous flight on a pre-programmed flight path. The purpose of the study was to use the unmanned aircraft "Fly Eye" by WB Electronic used by the Border Guard to patrol the state border in 103 TRA zone on the section of the Republic of Poland with the Kaliningrad District of the Russian Federation. The TRA zones constitute a specially designated area for the use of the Border Guard and the army, in order to carry out flights there beyond the scope of the pattern for training purposes and to patrol the state border. The article also contains information of the Border Guard formation and the characteristics of the unmanned aerial vehicle “FlyEye”. In order to ensure the safety of the UAV flight, the test was carried out in the TRA zone, which is used for special use for the Border Guard formation and the army.
    Źródło:
    Journal of KONES; 2018, 25, 4; 9-15
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-13 z 13

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