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    Wyświetlanie 1-13 z 13
    Tytuł:
    Sensitivity analysis for dynamic models of aerial munitions
    Autorzy:
    Żyluk, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/243173.pdf
    Data publikacji:
    2013
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aircraft
    air combat means
    dynamic properties of aerial bombs
    conditions on the aerial bomb’s flight path
    trajectory of aerial bombs
    Opis:
    While investigating dynamic properties of aerial bombs, both the analytical and experimental outcome often find their applications. Analysis of how a series of changes in flight parameters affect flight dynamics is probably one of the most essential efforts throughout this study. Numerical solutions of equations of motion deliver no information on the effect of changes in the aerial bomb’s design parameters on flight characteristics thereof. Therefore, the theory of sensitivity has been used in the paper to investigate the effect(s) of external disturbances, drop/release conditions and technical parameters on the aerial bomb’s range and flight path. Among other, the elements of the theory of sensitivity, equations of motion, numerical analysis of sensitivity of the bomb-describing mathematical model to changes in some selected parameters, numerical analysis of sensitivity of the bomb-describing mathematical model to changes in some selected parameters, analysis of the effect of changes in drop/release conditions on the aerial bomb’s flight path, analysis of the effect of changes in engineering (design) parameters of the aerial bomb on the trajectory thereof, effect of drop conditions on the aerial bomb’s range, effect of drop conditions on the side deflection of the aerial bomb’s trajectory are presented in the paper.
    Źródło:
    Journal of KONES; 2013, 20, 4; 517-523
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Feasibility of measurements in examination of air weapons
    Autorzy:
    Żyluk, A.
    Pietraszek, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/243450.pdf
    Data publikacji:
    2013
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aircraft
    air combat means
    flight tests of combat means
    data recorders for parameters of air combat means
    avionic bombs
    on-line data transmission systems
    Opis:
    Specific features of air weapons, dynamic examinations as an important component of the investigation process, examples of data recorders for parameters of the combat mean under test, telecommunication system for on-line data transmission with the assumption that the system should be composed of components and subassemblies that are commercially available from the market, system for RF transmission of flight parameters in the real time mode are presented in the paper. The system is made up of a transmitter and rpm sensors embedded into the head of the S-7 uncontrolled missile. Signals from the telecommunication module are received and decoded by means of a transducer with the sensitivity of about 2PV and stored in the memory of the TDS 3020 digital oscilloscope from Tektronix as well as in a four-channel digital recorder. The data acquisition system is triggered at the moment when the transmitter installed on the missile head was switched on. The missile was launched several seconds later. The paper includes among others workflow for examination of combat means, composition of measuring instruments for flight tests, data recorders for flight parameters installed on avionic bombs, signal waveforms recorded from rotation sensors and rotation speed variations for the S-7 missile during the flight
    Źródło:
    Journal of KONES; 2013, 20, 3; 451-460
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Method for estimating the static friction degree in the slide pair of the miniaturised electrohydraulic servomechanism
    Autorzy:
    Ułanowicz, L.
    Żyluk, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/245112.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    operation
    hydraulic drive
    electrohydraulic servomechanism
    pressure
    friction force
    Opis:
    One of the most important parameters specifying the usability of the miniaturised electrohydraulic servomechanism includes a static friction degree in its slide pairs, i.e. resistance of the slider’s movement from rest after some time of its staying at rest under pressure. Therefore, at the stage of designing and construction of the electrohydraulic servomechanism, it is important to determine the greatest static friction degree, which may arise in the slider hydraulic pair of this device during its operation. The objective of this article is to present a method for estimating the maximum static friction values in the slide pair based on the extreme value theory. The operation and loading conditions of the slide pair of the electrohydraulic servomechanism for the unmanned aircraft control system were described. The procedure for estimating the maximum static friction degree in the slide pair with the use of the extreme and probabilistic grid was presented. The extreme and probabilistic grid structure was based on the Gumbel probability graph. The graphic presentation of results of the static friction experimental studies in the slide pair on the extreme and probabilistic grid was discussed. By using the graphics method, the empirical dependence of the static friction force in the slide pair on the working fluid pressure in the hydraulic drive (loading conditions) was determined. A practical example of estimating the maximum values of the static friction force that may occur in the slider hydraulic pair of the miniaturized electrohydraulic servomechanism is shown.
    Źródło:
    Journal of KONES; 2018, 25, 2; 399-407
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    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:
    Simulation studies of micro air vehicle
    Autorzy:
    Sibilski, K.
    Zyluk, A.
    Kowalski, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/244124.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    construction of micro air vehicles
    simulation studies
    Opis:
    In the paper, we presented results of analysis of Micro Air Vehicle MAV stability on high Angle of Attack (AOA) by application continuation methods and bifurcation theory. Moreover, it presented two main tasks accomplished – performance analysis carried out, as well as numerical studies in order to find possible simplifications drive model, suitable for further design and analysis. This paper shows the typical MAV construction and their characteristics. Then presented results of calculations of necessary and required power (for CR3516 motor). The results shown in the Figure. The next step of MAV performance examination was calculations of dynamics stability and controllability of open loop system. Also shown state, and control matrixes for the longitudinal motion. Roots loci and open loop dynamics analysis for longitudinal motion are shown in the Figures. The next shown few function such as transfer function for the input (longitudinal velocity), transfer function for the pitch angular rate q input and for the lateral motion, state, and control matrices, etc. At the end shown results of simulations for dynamic response of MAV flight disturbance is shown in the Figure. The paper concluded short motions.
    Źródło:
    Journal of KONES; 2015, 22, 4; 243-252
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Studies and tests of micro aerial vehicle during flight
    Autorzy:
    Kowalski, M.
    Zyluk, A.
    Sibilski, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/245658.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    Micro Air Vehicle
    flight tests
    Opis:
    The article presents the results of flight tests of an unmanned flying device based on a model Micro Air Vehicle (MAV). The airplane was used during experimental studies. In the article, on-board equipment of micro-plane used in the study has been shown. Furthermore, the process of integrating all of the avionics equipment with MAV has been described. During the flight test, all parameters of microaircraft flight such as air and cruising speeds, altitude, air route, angles of tilt, slope angle, deviation angle, tilting speed, slope speed, deviation speed, etc. were recorded. During the study, the behaviour of micro-aircraft in various phases of flight such as autonomous take off, landing, programmable flight to the specific points of the air route was checked. In addition, the action of specified fail safe features of micro airplane operating in the case of a failure (e.g. in the case of low voltage of power package, loss of GPS signal, loss of communication with the ground station, etc.) is determined. The graphs of some flight parameters and figures of flight routes as well as flight profiles during the programmable flight have been presented. The researches allow for the verification of the integration process of micro-aircraft with on-board systems and they also allow for evaluation of its functional characteristics in further studies such as formation flights and bypassing the obstacles.
    Źródło:
    Journal of KONES; 2015, 22, 4; 155-162
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Experimental study and neural network modelling of aerodynamic and dynamic characteristics of flapping wings micro aerial vehicle
    Autorzy:
    Czekałowski, P.
    Sibilski, K.
    Żyluk, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/242331.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    entomopter
    flapping wings
    aerodynamics
    neural network
    modelling
    aerodynamika
    sieć neuronowa
    modelowanie
    Opis:
    The article is close connected with building flying object, that fly like an insect (entomopter). Present work concerns on concept of aerodynamic model using artificial neural networks. Model is used in simulations of flight of entomopter. Aerodynamic model based on experimental data. Necessary data are taken from experiment performed in water tunnel on entomopter model. For this case dynamic test are required. Measurements are ducted during sinusoidal motion of whole model. Modelled object is dipterous. Each wing can perform various spherical motions (wing is rotated around point). The motion of the wing in this case was two-dimensional; it was rotated around two axis. As a model, specially trained neural network is used. For training are used data from measurement. Presented in this article approach is based on artificial neural networks. In this article, innovative concept of model, describing unsteady aerodynamics of entomopter was proposed. It was shown that it could be easily implemented as mathematical model. Unsteady effects related to many state variables can be easily captured. Model can be easily adopted to predict different states of flight by networks training on appropriate data. Test has to reproduce real conditions as close, as it is possible. In reality, it is challenging to design test that will reproduce similar motion.
    Źródło:
    Journal of KONES; 2018, 25, 4; 49-57
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Modelling of physical phenomena in the vertical velocity measuring circuit for process of designing the SWPL-1 helmet-mounted display system
    Autorzy:
    Michalak, S.
    Żyluk, A.
    Szelmanowski, A.
    Borowski, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/243481.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    transport
    avionics
    helmet-mounted display systems
    error
    vertical velocity measurement
    Opis:
    The article presents the selected methods of identifying static and dynamic properties of the measuring paths to the extent necessary for the proper integration of on-board systems with the helmet-mounted flight parameter display system. It presents the methods of identifying static and dynamic properties of the WR-10MK on board variometer as one of more difficult identification elements. Its identification was carried out on the basis of the basic dependencies of the International Standard Atmosphere and the instruments construction’s parameters. It built a mathematical model describing the physical phenomena associated with vertical speed measurement. This model differs from the models found in the literature in terms of detail and description accuracy. On this basis, in the Simulink environment, it built a simulation model corresponding to its mathematical model. The non-linear model was the starting point for the construction of the linearized model based on the operator transmittance. The developed models were evaluated for errors of vertical speed’s dynamic indications. This allowed assessing the usefulness of the individual models for further works on ensuring the correlation of indications of the on-board variometer and the SWPL-1 helmet-mounted flight parameter display system. The presented simulation models include design details, as well as the characteristics of technological errors and disturbances of a stochastic nature. Another approach to the issue of identification is to use the characteristics provided by the manufacturer in the form of approximate characteristics of a module.
    Źródło:
    Journal of KONES; 2018, 25, 4; 277-284
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    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:
    Evaluation of the possibility of bomb flight control
    Autorzy:
    Kowaleczko, G.
    Olejniczak, E.
    Pietraszek, M.
    Żyluk, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/245642.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    airborne munitions
    bomb flight
    active bomb control
    aerodynamic bomb
    PRODAS calculations
    Opis:
    This paper presents theoretical model dedicated to a guided bomb. A mathematical description of the six-degrees-of-freedom motion of the bomb is shown. Particular attention was paid on aerodynamic forces and moments generated by additional control fins mounted on the front part of the bomb. Exemplary results of a numerical simulation of bombing are submitted and conclusions focused on the possibility of flightpath control are formulated. The paper concerns on the equations of bomb spatial motion and kinematic relations expressed making use of moving coordinate systems, the common origin of which is located at the centre of mass of the bomb. The set of equations of the rotating motion about the centre of mass in the body-fixed reference frame is presented. Aerodynamic forces and moments acting on the bomb are described. Coefficients are determined using the PRODAS software with detailed geometry of the LB-10M bomb. The coefficients were determined for different Mach numbers from 0.4 to 0.8. The important task was research investigations of aerodynamic characteristics with a wind tunnel and a set of experiments in real bombing conditions.
    Źródło:
    Journal of KONES; 2015, 22, 3; 105-115
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The design and simulation of an automated de-icing control system in the aircraft diamond DA42
    Autorzy:
    Gliwa, W.
    Żyluk, A.
    Grzesik, N.
    Kuźma, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/247354.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    anti-icing installation
    icing
    Diamond DA42
    aircraft
    general aviation
    MATLAB
    Opis:
    The article discusses the automatic control system of the Diamond DA42 aircraft anti-icing system. In the analysis of the issue of icing, four parameters were taken into account: air temperature, cloud humidity, temperature of the aircraft and precipitation. On the basis of the initial parameters, the authors determined the icing intensity, which is likely to occur on the aircraft skin. By automating the activities related to the activation of the de-icing system, it is possible to significantly relieve the pilot and increase the safety of air operations, particularly in conditions, which are conducive to the formation of icing. The authors performed a thirty-minute electronic simulation of the flight in real atmospheric conditions. The article discusses the obtained results of the simulation. Designed system uses fuzzy logic. The system inputs and output were determined and fuzzy expert inference system was developed in MATLAB software and Fuzzy Logic Toolbox. The proper system work was verified with use of MATLAB/Simulink software. Use of that kind of systems can significantly relieve the pilot and increase the safety of air operations, particularly in conditions, which are conducive to the formation of icing.
    Źródło:
    Journal of KONES; 2018, 25, 4; 525-532
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Aerodynamic measurements micro air vehicle
    Autorzy:
    Zyluk, A.
    Sibilski, K.
    Kowalski, M.
    Wiśniowski, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/243837.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    construction of micro air vehicles
    aerodynamic measurements
    Opis:
    In present times, constructions of micro air vehicles arouse more and more interest researchers and manufacturers. Air turbulence is perceived as a major problem for Micro Air Vehicles (MAV) in outdoor applications. According to the literature, short duration vertical gusts may have velocity comparable to MAV airspeed, so brief periods of flight at very large angles of attack have to be considered. In these circumstances, it seems reasonable to apply the design with as high stall angle of attack as possible. In particular, the flow has to be attached to control surfaces to perform effective control in order to damp air turbulence effect. Therefore, an aircraft configuration was developed with cranked delta wing and propeller located inside the wing contour. To prove the value of the concept, wind tunnel experiment was undertaken. The prototype demonstrated ability to fly controllably at extremely high angles of attack. Moreover we present few disadvantages of these construction for example it was very sensitive to the motor settings, since every rpm change required immediate airplane trimming to maintain straight path of flight. This drawback can be eliminated by application of counter-rotating propeller. The status of the program is presented in the paper, including the most recent results, as well as currently undertaken experiments and plans for the nearest future.
    Źródło:
    Journal of KONES; 2015, 22, 4; 343-353
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The evaluation of the efficiency of active control system for aerial bomb
    Autorzy:
    Kowaleczko, G.
    Żyluk, A.
    Pietraszek, M.
    Wijaszka, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/244285.pdf
    Data publikacji:
    2018
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    simulation
    PID controller
    laser-guided bombs
    Opis:
    The article presents the results of numerical simulation of a laser-guided bomb, which is dropped in calm weather conditions. The prototype of such a bomb was developed at the Air Force Institute of Technology. It was a result of the modification process of the classical training bomb. The modification consisted of building on the bomb's board a detection system to track targets that are designated by laser and a control system to adjust bomb’s glide path to precisely strike the target. In the simulation research, geometric and mass characteristics of the classical training bomb were used. Aerodynamic characteristics of the bomb have been determined using commercial software PRODAS. Using the mathematical model of the bomb spatial motion and model of the laser detection system series of simulations were performed. The main goal was to determine the effectiveness of the adopted construction solution. Therefore, simulations were performed for various initial positions of the bomb and fixed position of the target. It allowed finding the set of control laws coefficients giving the most accuracy of the bomb. The influence of structural modifications of the detection system on the possibility of effective detection and location of the target was also investigated. In the article, exemplary results of numerical calculations performed with the author's software are also shown.
    Źródło:
    Journal of KONES; 2018, 25, 4; 165-174
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-13 z 13

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