Temat: aircraft dynamics - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Sliding mode control for longitudinal aircraft dynamics
Autorzy:: Iskrenovic-Momcilovic, O.
Powiązania:: https://bibliotekanauki.pl/articles/385149.pdf
Data publikacji:: 2018
Wydawca:: Sieć Badawcza Łukasiewicz - Przemysłowy Instytut Automatyki i Pomiarów
Tematy:: aircraft dynamics
control
elevator
longitudinal
sliding mode
Opis:: The control of the longitudinal aircraft dynamics is challenging because the mathematical model of aircraft is highly nonlinear. This paper considers a sliding mode control design based on linearization of the aircraft, with the pitch angle and elevator deflection as the trim variables. The design further exploits the decomposition of the aircraft dynamics into its short-period and phugoid approximations. The discrete-time variable structure system synthesis is performed on the base of the elevator transfer function short-period approximation. This control system contains a sliding mode controller, an observer, based on nominal aircraft model without finite zero and two additional control channels for the aircraft and for the aircraft model. The realised system is stable and robust for parameter and external disturbances.
Źródło:: Journal of Automation Mobile Robotics and Intelligent Systems; 2018, 12, 3; 55-60
1897-8649
2080-2145
Pojawia się w:: Journal of Automation Mobile Robotics and Intelligent Systems
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Innovationality is the transfer process from the idea to commercialization
Autorzy:: Wiśniewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/243893.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: ground vibration test
modal analysis
aircraft structure dynamics
Opis:: In today's world, innovationality is synonymous with modernity, development, good governance and strategic thinking. The country 's economy and whole of society should be innovative. The research and development process and the results of the work would be reviewed from the commercialization perspective. The all innovative projects should finish on thefree market, but majority of them end their lives at the research and development stage. The idea of spin-off corporations has to serve the subordination of the entire innovative project realization cycle to the vision of its commercialization. Innovative society and economy require implementation of both large and small innovations, created in large, medium and small R & D programs. In economically leading countries, the mega-programs play an important role in innovationality. small innovation programs are usually created by small research teams and individual inventors. For the balanced development of the country's economy, there is a needfor the variety, both small and large innovation programs. In the absence of an effective opportunity to realize one's own Polish mega-programs, it is worth to consider the mega-program named: ,,Provision of services on the International research market" as a Polish specialty. For 10 years the Warsaw's Institute of Aviation pursues this strategy. The Institute of Aviation employs about 800 specialists, which perform the advanced research of the new materials and designs for the new gas turbine engines and combustion systems.
Źródło:: Journal of KONES; 2010, 17, 1; 485-488
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Effect of changes in some design parameters on the dynamic properties of aircraft
Autorzy:: Wiśniewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/243891.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: ground vibration test
modal analysis
aircraft structure dynamics
Opis:: The aim of the study presented in the paper was to examine the impact of changes related to aircraft modernization, the dynamic properties of an aircraft on the basis of five cases studied experimentally. Which changes in the dynamics of an aircraft structure occurred as a result of modernization can be experimentally tested by resonance tests. For this purpose, resonance tests should be carried out before the aircraft modernization and after its completion. In order to mapping the conditions of free flight the objects were suspended flexibly. The electrodynamics actuators were used to induce vibrations, piezoelectric transducers were used for the measurement of vibrations. The size and phase of extortion forces and their application points were selected individually for each resonance in order to get the best separation of it. The first stage of the study was based on recordings the frequency - amplitude characteristics. The second stage of the study was the Identification of individual frequencies and mode shapes of each resonance, which was implemented by choosing the size and the proportion of mutual phase shifts between the extortion forces. In the selection the criteria based on minimizing the phase difference of vibrations measured at several points of the structure were used. The final stage of this study was to register the frequency and shapes mode of the tested resonance and the resonance generalized masses and damping coefficients.
Źródło:: Journal of KONES; 2010, 17, 1; 479-483
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Development of a flight simulator for conceptual aircraft design and sizing
Autorzy:: Hon, Kai San
Karpuk, Stanislav
Yang, Daqing
Elham, Ali
Powiązania:: https://bibliotekanauki.pl/articles/36455876.pdf
Data publikacji:: 2022
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: flight dynamics
flight simulation
aircraft design
Opis:: This article describes the development of a flight simulator module within the ADEMAO aircraft design framework to investigate the effects of novel airframe and propulsion technologies on new generations of aircraft. Methods used to develop and integrate the fight simulator into the overall design framework are described. The simulator is validated based on existing data from the Convair CV-880M and is then used to analyze an example case of a conceptual medium-range aircraft with advanced airframe technologies designed in the Sustainable and Energy-Efficient Aviation research cluster at the Institute of Aircraft Design and Lightweight Structures at the Technische Universität Braunschweig. Results show the deficiencies of the medium-range aircraft in short-period pitch and Dutch roll performance, and recommendations for modifications to the conceptual medium-range aircraft are drafted.
Źródło:: Transactions on Aerospace Research; 2022, 2 (267); 31-61
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Analysis of 1st stage compressor rotor blade stress and vibration amplitudes in one-pass jet engine
Autorzy:: Szczepanik, R.
Powiązania:: https://bibliotekanauki.pl/articles/244813.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostics of aircraft engines
compressor blade dynamics
Opis:: This paper considers 1st stage compressor blade dynamics in the one-pass jet engines of trainer aircraft. Research was carried out on an engine test bench using the SAD system and its results were compared with those obtained using the tensometric approach. In this paper presented basic dynamic properties of rotor blades, bench test of rotor blade dynamics, Bench tests of the dynamic behaviour of blades subjected to external impacts and then Comparison of strain gauge and SAD tip-timing results. Then discusses the results of tests assessing the accuracy of the 1987 ITWL device by comparing strain gauge signals with those recorded by SAD apparatus in a running engine. It also presented simultaneous vibration readings of all the rotor blades at selected rotation speeds. Also shows that increased stress in these blades may be due to repeated engine surges, normal and hot engine surges, entry into the engine of a foreign object. Among others selection and layout of rotor blades in the 1st stage of a one-pass engine compressor, stress amplitudes for rotor blade, stress in rotor blade, stress amplitudes, free inlet flow and smooth engine acceleration, vibration amplitudes, asynchronous vibrations are presented in the paper.
Źródło:: Journal of KONES; 2013, 20, 4; 441-450
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Examination of the dynamic properties of 1st stage rotor blades in one - pass engine compressors under operating conditions
Autorzy:: Szczepanik, R
Powiązania:: https://bibliotekanauki.pl/articles/242705.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostics of aircraft engines
compressor blade dynamics
Opis:: This article includes studies of vibration and stress amplitudes in the Is' stage rotor blades of jet trainer one-pass engine compressors before and after refurbishment in operating conditions. The presented results were obtained using SAD-2 blade vibration amplitude registering and measuring apparatus. The same tests were carried on the same one-pass engine after modernisation. Example oscillograms from the vibration tests of the 16 blades are shown in this article, where show the vibrations of three randomly selected one-pass engines after refurbishment (marked 1, 2 and 3) out of a total of 50 engines. The engine vibration spectra cover the full rotation speed range. The difference between the vibration amplitudes of 1st stage rotor blades, in one-pass engine compressors before and after the refurbishment, is results from the difference in how the blades were attached to the disc. Before modernisation the hammer-type root was used, whereas after refurbishment dovetail-type fittings were applied. Furthermore, it was confirmed that there is nocoupling via the blade disc occurred when the blades were arranged on the disc according to the sinusoidal order of their free vibration frequencies. In such cases recorded vibration amplitudes remain within the average range (from 100 to 120 MPa in terms of stress).
Źródło:: Journal of KONES; 2013, 20, 3; 395-404
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Dynamics and control of a gyroscope-stabilized platform in a self-propelled anti-aircraft system
Dynamika i sterowanie platformy giroskopowej s samobieżnym zestawie przeciwlotniczym
Autorzy:: Korupa, Z.
Dziopa, Z.
Krzysztofik, I.
Powiązania:: https://bibliotekanauki.pl/articles/280132.pdf
Data publikacji:: 2010
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: anti-aircraft system
gyroscope
dynamics and control
gyroscope-stabilized platform
Opis:: The paper presents a mathematical model of a triaxial gyroscopic platform on a moving platform base (motor vehicle). Control software plat forms are designated with the inverse dynamics of the duties, while the control correction - using the LQR method. The considered platform can be used as an independent observation base for systems, cameras, parcels or gun machines. In the present study, it is shown in its application to stabilization of anti-aircraft missile launchers.
W pracy przedstawiony jest model matematyczny trzyosiowej platformy giroskopowej na ruchomej podstawie (pojeździe samochodowym). Sterowania programowe platformy wyznaczone są z zadnia odwrotnego dynamiki, natomiast sterowania korekcyjne - za pomocą metody LQR. Rozpatrywana platforma może znaleźć zastosowanie jako niezależna pdstawa dla układów obserwacyjnych, kamer, działek czy też karabinie maszynowych.W niniejszym opracowaniu pokazane jest jej zastosowanie do stabilizacji wyrzutni przeciwlotniczych pocisków rakietowych.
Źródło:: Journal of Theoretical and Applied Mechanics; 2010, 48, 1; 5-26
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Investigation of influence of aircraft propeller modal parameters on small airplane performance
Badania wpływu modalnych parametrów śmigła na zachowanie małego samolotu
Autorzy:: Kilikevičius, Arturas
Rimša, Vytautas
Rucki, Mirosław
Powiązania:: https://bibliotekanauki.pl/articles/301179.pdf
Data publikacji:: 2020
Wydawca:: Polska Akademia Nauk. Polskie Naukowo-Techniczne Towarzystwo Eksploatacyjne PAN
Tematy:: aircraft propeller
dynamics
vibration
operational modal analysis
śmigło lotnicze
dynamika
wibracje
analiza modalna
Opis:: The aim of the current paper is to investigate a small airplane model propeller of class F2D according to requirements of Fédération Aéronautique Internationale (FAI, or World Air Sports Federation). In some cases, practical tests show that F2D models with flexible propellers produce specific extra noise and increase flight speed in comparison with “rigid” propellers. Therefore, the following hypothesis could be proposed: flexible characteristics of the increased noise are related to the resonant eigenfrequencies of the propeller. The operating range of the F2D class propeller (28,000-35,000 rpm) is close to or equal to the eigenfrequency resonance. The current investigation addresses dynamic/flexible vibrations of elastic propeller during engine run and researches dynamic parameters of the propeller as well as the contribution of these parameters to the model flight characteristics. To resolve this type of a problem, a stand, which allows completing a physical investigation of flexible propeller vibration modes and dynamic characteristics was created.
Celem artykułu jest przedstawienie wyników badań śmigła małego modelu samolotu zaliczanego do klasy F2D (według klasyfikacji Fédération Aéronautique Internationale, FAI). W niektórych przypadkach testy wykazały, że modele F2 z giętkimi śmigłami, w porównaniu do śmigieł sztywnych, wydają dodatkowy hałas i zwiększają prędkość samolotu. Dlatego wysunięto hipotezę, że elastyczne charakterystyki zwiększonego hałasu są powiązane z rezonansem częstotliwości własnych śmigła. Zakres pracy śmigła klasy F2D (28 000-35 000 obr/min) jest zbliżony do jego częstotliwości własnych. Badania dotyczą elastycznych wibracji dynamicznych śmigła giętkiego w czasie rozruchu silnika i są nakierowane na wyznaczanie parametrów dynamicznych i ich wpływu na charakterystyki lotu modelu. Wykonano i opisano stanowisko, na którym przeprowadzono testy modalne drgań giętkiego śmigła. Na tej podstawie uzyskano charakterystyki dynamiczne.
Źródło:: Eksploatacja i Niezawodność; 2020, 22, 1; 1-5
1507-2711
Pojawia się w:: Eksploatacja i Niezawodność
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Modelling and analysis of shell case dynamics
Modelowanie i analiza dynamiki lotu łuski
Autorzy:: Manerowski, J.
Nowakowski, M.
Powiązania:: https://bibliotekanauki.pl/articles/281200.pdf
Data publikacji:: 1998
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: aircraft gun shell
model of dynamics of a shell case
zone of dispersion of a shell case
Źródło:: Journal of Theoretical and Applied Mechanics; 1998, 1; 145-161
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Simulation of rime icing and its effects on aerodynamic characteristics of an airfoil
Autorzy:: Sznajder, J.
Powiązania:: https://bibliotekanauki.pl/articles/243475.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: computational fluid dynamics
aerodynamics
two-phase flow
simulation of ice accretion
heat exchange
aircraft engineering
transport
vehicle
Opis:: A mathematical model for simulation of icing dedicated to simulation of ice accretion and its effects on aircraft aerodynamic characteristics in conditions of rime icing is presented. Pure rime icing occurs at lower temperatures than glaze icing and results in higher roughness of the surface of deposited ice. The model accounts for increased surface roughness, in terms of equivalent sand grain roughness, caused by deposited rime ice, which influences generation and dispersion of heat in the boundary layer. Increase of surface roughness is determined by analytical models created upon experimental data obtained in icing wind tunnels. Increased generation of heat is a result of increased tangential stress on the surface and is quantified in the temperature recovery factor determined numerically by a CFD solver. Effects of surface roughness on the intensity of forced convection are quantified by application of Colburn analogy between heat and momentum transfer in the boundary layer, which allows assessment of heat transfer coefficient for known friction coefficient, determined by CFD. The computational method includes determination of the surface distribution of mass of captured water in icing conditions. The model of freezing of captured water accounts for generation of heat due to latent heat of captured water droplets, temperature recovery in boundary layer and kinetic energy of captured droplets. The sinks of heat include forced convection, heating of super cooled droplets, conduction of heat through the ice layer and sublimation. The mathematical model is implemented as user-defined function module in ANSYS Fluent solver. The results include effects of deposited ice, including increased surface roughness on aerodynamic characteristics of an airfoil.
Źródło:: Journal of KONES; 2018, 25, 3; 437-443
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Modelowanie katapultowania w układzie przestrzennym
The mathematical modeling of spatial ejection
Autorzy:: Głowiński, S.
Powiązania:: https://bibliotekanauki.pl/articles/312013.pdf
Data publikacji:: 2013
Wydawca:: Instytut Naukowo-Wydawniczy "SPATIUM"
Tematy:: samolot
dynamika lotu
modelowanie procesu katapultowego
fotel katapultowy
katapultowanie
trajektoria lotu fotela katapultowego
ejection simulation modelling
aircraft
ejection seats
catapulting trajectory of ejection seat
flight dynamics
Opis:: Artykuł przedstawia metodykę postępowania przy określaniu układów współrzędnych w procesie katapultowania. Poprzez właściwe i jednoznaczne stosowanie oznaczeń istnieje możliwość jasnego określania położenia fotela katapultowego względem samolotu i względem ziemi. O ile w przypadku układu symetrycznego zadanie nie jest trudne, w przestrzeni dochodzą kąty ślizgu i przechylenia oraz siły i momenty, które mają decydujący wpływ na trajektorię fotela. Autor poprzez wprowadzenie dodatkowych układów współrzędnych oraz określenie macierzy transformacji pomiędzy tymi układami, ujednolica stosowane oznaczenia i zwraca uwagę na związki pomiędzy prędkościami liniowymi i kątowymi tych układów.
The paper presents the methodology followed for determination of coordinate systems in the ejection process. The using of appropriate and clear signs it is possible to clearly determining of the position of the ejection seat relativity the plane and the ground. While in the case of the symmetrical task is not difficult in space come sliding and tilting angles and the forces and moments that have a decisive influence on the trajectory of the seat. Author by introducing additional coordinate systems and to determine the transformation matrix between the two systems, standardizes used signs and draws attention to the relationship between linear and angular velocities of these systems.
Źródło:: Autobusy : technika, eksploatacja, systemy transportowe; 2013, 14, 3; 115-122
1509-5878
2450-7725
Pojawia się w:: Autobusy : technika, eksploatacja, systemy transportowe
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Investigation of thermal interactions between elements of propulsion system and selected parts of the airplane skin in small aircrafts
Autorzy:: Łapka, P.
Seredyński, M.
Furmański, P.
Powiązania:: https://bibliotekanauki.pl/articles/240885.pdf
Data publikacji:: 2018
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: computational fluid dynamics
numerical heat transfer
propulsion system
small aircraft
thermal interactions
CFD
numeryczna mechanika płynów
numeryczna wymiana ciepła
układ napędowy
samolot lekki
interakcje termiczne
Opis:: Development of new or upgrading of existing airplanes requires many different analyses, e.g., thermal, aerodynamical, structural, and safety. Similar studies were performed during re-design of two small aircrafts, which were equipped with new turboprop engines. In this paper thermo-fluid analyses of interactions of new propulsion systems with selected elements of airplane skin were carried out. Commercial software based numerical models were developed. Analyses of heat and fluid flow in the engine bay and nacelle of a single-engine airplane with a power unit in the front part of the fuselage were performed in the first stage. Subsequently, numerical simulations of thermal interactions between the hot exhaust gases, which leave the exhaust system close to the front landing gear, and the bottom part of the fuselage were investigated. Similar studies were carried out for the twin-engine airplane with power units mounted on the wings. In this case thermal interactions between the hot exhaust gases, which were flowing out below the wings, and the wing covers and flaps were studied. Simulations were carried out for different airplane configurations and operating conditions. The aim of these studies was to check if for the assumed airplane skin materials and the initially proposed airplane geometries, the cover destruction due to high temperature is likely. The results of the simulations were used to recommend some modifications of constructions of the considered airplanes.
Źródło:: Archives of Thermodynamics; 2018, 39, 3; 45-61
1231-0956
2083-6023
Pojawia się w:: Archives of Thermodynamics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Dynamika statku powietrznego i fotela katapultowego w układzie przestrzennym
Aircraft and ejection seat dynamics in three-dimensional space
Autorzy:: Głowiński, S.
Powiązania:: https://bibliotekanauki.pl/articles/312018.pdf
Data publikacji:: 2013
Wydawca:: Instytut Naukowo-Wydawniczy "SPATIUM"
Tematy:: samolot
modelowanie procesu katapultowego
fotel katapultowy
katapultowanie
MATLAB/Simulink
trajektoria lotu fotela katapultowego
ejection simulation modelling
aircraft
MATLAB Simulink
ejection seats
catapulting trajectory of ejection seat
flight dynamics
Opis:: Artykuł przedstawia model matematyczny dynamiki statku powietrznego i fotela katapultowego. Przeprowadzono symulację wybranego typu fotela katapultowego z uwzględnieniem zmiany masy pilota i prędkości lotu statku powietrznego przy wykorzystaniu pakietu MATLAB ze szczególnym uwzględnieniem przelotu nad statecznikiem pionowym samolotu.
Paper discussed the mathematical model of dynamics of the aircraft and ejection seat. The numerical simulation on the selected type of ejection seat in function of pilot mass and speed of aircraft by using MATLAB package with a particular focus on the vertical stabilizer plane was studied.
Źródło:: Autobusy : technika, eksploatacja, systemy transportowe; 2013, 14, 3; 173-181
1509-5878
2450-7725
Pojawia się w:: Autobusy : technika, eksploatacja, systemy transportowe
Dostawca treści:: Biblioteka Nauki

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