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Tytuł:
Neural-sliding mode augmented robust controller for autolanding of fixed wing aircraft
Autorzy:
Ismail, I.
Pashilkar, A. A.
Ayyagari, R.
Sundararajan, N.
Powiązania:
https://bibliotekanauki.pl/articles/91533.pdf
Data publikacji:
2012
Wydawca:
Społeczna Akademia Nauk w Łodzi. Polskie Towarzystwo Sieci Neuronowych
Tematy:
controller
nonlinear dynamic inversion
control signal
phase compensator
antiwindup scheme
wing aircraft
autolanding
Opis:
Neural and sliding mode controllers are generally based on the principle of nonlinear dynamic inversion. This leads to control signals containing high frequency components. This can result in actuator rate limiting due to loss of phase at higher frequencies. Large control inputs, for example due to the saturation component of the sliding mode controller can also result in position saturation of the actuator. In this paper we show that by the introduction of suitable phase compensators and an antiwindup scheme the neuralaided sliding mode controller performance can be improved. A novel scheme is proposed for the cascaded feedback controller which addresses practical requirements of both state limiting and control surface saturation respectively.
Źródło:
Journal of Artificial Intelligence and Soft Computing Research; 2012, 2, 4; 317-330
2083-2567
2449-6499
Pojawia się w:
Journal of Artificial Intelligence and Soft Computing Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Ground effect influence on the aerodynamic characteristics of ultralight high-wing aircraft : wind tunnel tests
Autorzy:
Placek, R.
Ruchała, P.
Stryczniewicz, W.
Powiązania:
https://bibliotekanauki.pl/articles/241907.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
ground effect
aerodynamic characteristics
high-wing ultralight aircraft
wind tunnel research
Opis:
The ground proximity may significantly improve the performance of the aircraft, but in some conditions, it affects its stability. The gain of lift which and reduction of drag during low altitude flight is known as the wing in ground effect (WIG effect). It may concern aircrafts or WIG-crafts (ground effect vehicles). In the article experimental results of the wind tunnel test of an aircraft in ground effect has been presented. The main aim of the test was to investigate the ground effect influence on aerodynamic characteristic of the of the ultralight high-wing aircraft model during early take off, taxiing or final landing stage. Investigation was carried out in the 1.5 m diameter low speed T-1 wind tunnel in the Institute of Aviation in Warsaw. The velocity was 32 m/s and Reynolds number related to the aerodynamic chord was equal about 0.37·106. Tests were performed for chosen angles of attack in range 0-10⁰. During investigation, the strain gauge balance measurements and Particle Image Velocimetry (PIV) flow visualization technique were applied. Tested model position was relatively close to the ground. It was found, that the ground proximity has significant influence on the pitching moment. The normal force was increased and the axial force is decreased due to the WIG effect, which is compatible with the theory. It has significant meaning for control aircraft issue and safety.
Źródło:
Journal of KONES; 2017, 24, 2; 183-190
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
An automated CAD/CAE integration system for the parametric design of aircraft wing structures
Autorzy:
Benaouali, A.
Kachel, S.
Powiązania:
https://bibliotekanauki.pl/articles/280488.pdf
Data publikacji:
2017
Wydawca:
Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:
CAD/CAE integration
design automation
aircraft wing
parametric design
Opis:
In order to take advantage of the sophisticated features offered by CAD and CAE packages for modeling and analysis during the design process, it is essential to build a bridge assuring a coherent link between these tools. Furthermore, this integration procedure must be automated so as to get rid of the repetitive costing effort. In this paper, a new automated procedure for the CAD/CAE integration, implemented for the parametric design and structural analysis of aircraft wing structures is presented. This procedure is based on the automation capacity available in modern computer aided tools via build-in basic programming languages as well as the capacity of the model data exchange. The geometric and numerical models can be controlled to generate a large variety of possible design cases through parameters introduced beforehand.
Źródło:
Journal of Theoretical and Applied Mechanics; 2017, 55, 2; 447-459
1429-2955
Pojawia się w:
Journal of Theoretical and Applied Mechanics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Aircraft wing structural design application in MATLAB App Designer
Autorzy:
Bilal, Ahmed
Siddiqui, Faisal
Abbas, Messam
Mansoor, Mohtashim
Powiązania:
https://bibliotekanauki.pl/articles/29520093.pdf
Data publikacji:
2021
Wydawca:
Akademia Górniczo-Hutnicza im. Stanisława Staszica w Krakowie. Wydawnictwo AGH
Tematy:
automated aircraft wing design
aircraft preliminary design phase
wing structure
analytical method
bending
torsional stiffness
MATLAB App Designer
Opis:
This study focuses on developing an automated application in the MATLAB® App Designer module, based on basic structural members and different theories for various loading cases, providing ballpark values of bending and torsional stiffness and sizing of the load-carrying structural member at a span wise location. All the code developed on MathWorks (2018) is automated using the App Designer module. In this approach, governing equations of structural members under different types of loading are solved in MATLAB IDE with the assumption that in the preliminary phase MATLAB App Designer provides an easy drag and drop type application developer that can be easily subsumed in any mathematical automation process.
Źródło:
Computer Methods in Materials Science; 2021, 21, 4; 193-202
2720-4081
2720-3948
Pojawia się w:
Computer Methods in Materials Science
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analiza możliwości zastosowania skoku cyklicznego na smigle pchającym w układach wiropłatów zespolonych typu wiatrakowiec
Analysis of adaptation periodic pitch puscher propeller in compound rotary-wing aircraft
Autorzy:
Paszko, P.
Powiązania:
https://bibliotekanauki.pl/articles/212980.pdf
Data publikacji:
2011
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
skok cykliczny
zastosowania
smigło pchające w układach wiatropłatów
wiropłaty zespolone typu wiatrakowiec
adaptation periodic pitch pusher propeller
compound rotary-wing aircraft structures
autogyro
Opis:
W pracy została przedstawiona modyfikacja konstrukcji i sposobu działania śmigła pchającego. Koncepcja nowego rodzaju śmigła została poparta wstępnymi obliczeniami momentów powstających na śmigle, wywołujących zmianę kierunku lotu wiatrakowca, oraz analizą opływu w obszarze śmigła. Projekt koncepcyjny opiera się o istniejące rozwiązania stosowane na śmigłowcach. Do rozwiązań tych można zaliczyć: sterowania kątem nastawienia łopat za pomocą popychaczy przechodzących przez wał śmigła (Enstrom F-28 [2]), oraz mocowaniem śmigła na nieruchomej tulei wzmacniającej wał śmigła (AH-64 Apache [4]).
This work contains introduction of construction and functioning modification of pusher propeller. New conception of propeller has been supported by initial calculations of steering moment created on propeller, which influence flight direction of autogyro and also analysis of flow in propeller field. Predesign is based on existing solutions applied to modern helicopters. Applied solutions are as follows: steering of blade position by means of pushers, which are going axially through the propeller shaft (Enstrom F-28), fixing propeller on the stiff sleeve strengthening the propeller shaft (AH-64 Apache).
Źródło:
Prace Instytutu Lotnictwa; 2011, 10 (219); 257-268
0509-6669
2300-5408
Pojawia się w:
Prace Instytutu Lotnictwa
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analiza odkształceń kompozytowego skrzydła samolotu
Analysis of deflection of composite aircraft wing
Autorzy:
Stadnicki, J.
Tokarz, Z.
Powiązania:
https://bibliotekanauki.pl/articles/209114.pdf
Data publikacji:
2008
Wydawca:
Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:
kompozyt warstwowy
model MES
skrzydło samolotu
wytrzymałość konstrukcji lotniczych
laminar composite
FEM model
aircraft wing
strength of aircraft constructions
Opis:
W artykule przedstawiono modele obliczeniowe skrzydła samolotu EM-11 ORKA wykonanego z kompozytu warstwowego wzmacnianego tkaniną z włókien węglowych. Modele zbudowano z wykorzystaniem metody elementów skończonych, uwzgledniono strukturę wewnetrzną kompozytu na poziomie jego komponentów: wzmocnienia - tkaniny i osnowy - żywicy. W modelach MES zastosowano elementy powłokowe i superelementy. Wyniki obliczeń ugięć skrzydła porównwno z wynikami pomiarów stanowiskowych.
Calculation models of wing of ORKA aircraft, which is made of composite material reinforced by fabric of carbon fibers, are presented in the paper. The models are constructed using finite elements method, the inner structure of the composite material in the level of its components: reinforment - fabric and resin matrix has been taken into account. Shell elements and superelements are used in the FEM models. The calculation results of wing deflection of have been compared to the results of experimental measurements.
Źródło:
Biuletyn Wojskowej Akademii Technicznej; 2008, 57, 2; 45-54
1234-5865
Pojawia się w:
Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Promising wing vibration measurement system using MEMS IMUS and Kalman filter correction
Autorzy:
Maamo, M. S.
Afonin, A. A.
Sulakov, A. S.
Powiązania:
https://bibliotekanauki.pl/articles/2174203.pdf
Data publikacji:
2022
Wydawca:
Uniwersytet Zielonogórski. Oficyna Wydawnicza
Tematy:
skrzydło samolotu
drgania
filtr Kalmana
aircraft wing
vibration measurement
Kalman filter
MEMS IMU
closed-loop optimal correction
Opis:
Nowadays, there is still a need for the development of a high-precision vibration measurement system for aircraft wings. By analyzing the wing vibration characteristics a lot of aviation studies could be conducted, including the wing health monitoring, the fluttering phenomenon and so on. This paper presents preliminary results of the research carried out toward building a promising system designed to measure vibration parameters of aircraft wing. Comparing it with the existing analogue systems, the proposed system features the use of approaches that are traditional for solving orientation and navigation problems for vibration measurements. The paper presents the basic structure of the system, the fundamentals of its operation, the mathematical errors models of its main components, the correction algorithms using optimal Kalman filter. Finally, the initial simulation results of system operation are shown, demonstrating the expected accuracy characteristics of the system, which confirms its effectiveness and the prospects of the chosen direction of research.
Źródło:
International Journal of Applied Mechanics and Engineering; 2022, 27, 2; 143--157
1734-4492
2353-9003
Pojawia się w:
International Journal of Applied Mechanics and Engineering
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The influence of wing transverse vibrations on dynamic parameters of an aircraft
Wpływ drgań giętnych skrzydła na dynamiczne parametry lotu samolotu
Autorzy:
Wachłaczenko, M.
Powiązania:
https://bibliotekanauki.pl/articles/280033.pdf
Data publikacji:
2010
Wydawca:
Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:
wing vibrations
aircraft
sumulation
Opis:
The paper presents numerical analysis of airplane parameters of motion during wing transverse vibrations of an average commercial airplane. The mathematical model of the airplane motion including a system of twelve ordinary differential equations was employed. Using available publications and M28 "Bryza" airplane geometrical and mass relationships, a computer code evaluating parameters of the motion was developed. In order to take the wing transverse vibrations under consideration, the way of wing displacements in the aircraft-fixed system of coordinates was elaborated as well as vibration amplitude and frequency were assumed. The analysis covered two cases of wing transverse vibrations: bending of both wing halves in phase and in counter-phase. On the basis of the obtained results, some conclusions referring the airplane dynamic properties during wing vibrations were formulated.
W pracy przedstawiono wyniki numerycznej symulacji drgań giętnych skrzydła samolotu dyspozycyjnego. Zastosowano klasyczny model matematyczny dynamiki ruchu samolotu, opisany przez układ dwunastu równań różniczkowych pierwszego rzędu. W celu uwzględnienia drgań skrzydła zamodelowano sposób przemieszczania się elementów skrzydła w samolotowym układzie współrzędnych oraz założono częstotliwość i amplitudę drgań skrzydła. Analizę przeprowadzono dla dwóch przypadków zginania skrzydła: zginanie połówek skrzydła w fazie i w przeciwfazie. Na podstawie analizy opracowano wnioski dotyczące własności dynamicznych samolotu podczas drgań jego powierzchni nośnych.
Źródło:
Journal of Theoretical and Applied Mechanics; 2010, 48, 2; 397-413
1429-2955
Pojawia się w:
Journal of Theoretical and Applied Mechanics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Study on Possible Replacement of the Aluminum Spar with a Composite Structure Illustrated with the Case of Agricultural Aircraft
Autorzy:
Fałek, M.
Szymczyk, E.
Jachimowicz, J.
Powiązania:
https://bibliotekanauki.pl/articles/98018.pdf
Data publikacji:
2017
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
composite structure
agricultural aircraft
airplane wing
Opis:
Composite materials are increasingly being used in aviation. Specific stiffness and strength of composite materials (especially CFRP laminate, sandwich structure) are higher compared to metal alloys. They are beneficial features of materials used in aviation. Mass reduction of aircraft structures (e.g. due to the use of composite materials) contributes to an aircraft’s better performance in terms of its range, top speed and ceiling and consequently causes an increase in airplanes capacity. Moreover, the use of high-strength and lightweight materials in aviation contributes to longer life time and lower exploitation costs. The aim of the paper was the study the possibilities of replacing the aluminum spar of an airplane wing with a composite structure. In order to compare the mass and strength of the aluminum with the composite spar, the global shell and local solid models were created and finite elements analysis was performed. The analysis was carried out for the front spar of the wing of the agricultural aircraft PZL-106.
Źródło:
Fatigue of Aircraft Structures; 2017, 9; 85-99
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Resonance tests - vibration mode shapes from the wing torsion group
Autorzy:
Wiśniewski, W.
Powiązania:
https://bibliotekanauki.pl/articles/245897.pdf
Data publikacji:
2009
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
transport
aircraft
resonance tests
vibration mode
torsion wing
Opis:
Resonances of the „ wings torsion " mode shapes to a large extent depend on the structural parameters of the wing, and more specifically to the existence or not of fuel tanks at the wings ends, munitions hard points or engines mounted on the wings. In the paper the group of resonances is presented with mode shapes in which the one, two or three node aircraft wing torsion is present. It is shown in the paper, that these vibration mode shapes consist both of fuselage bending or torsion. Resonance frequencies with mode shapes in which one, two or three node wing torsion occurs depend fundamentally on existence of wing hardpoints. If hardpoints are occupied by fuel tanks, these frequencies are varying continuously in wide range. The various interesting from cognitive point of view combinations have place then, including variable frequencies and variable mode shapes as a function of fuel consumption. The aim for the analysis of 3 cases of resonance a wing torsion mode shapes of airplanes and gliders was to investigate the relationships and mechanisms that are taking place and operate between the torsioningl vibration of the wings and bending or torsion vibrations of the fuselage. Recognition of these phenomena should facilitate the researcher to understand and search effectively and explore the resonances of„ wing torsion " mode shapes.
Źródło:
Journal of KONES; 2009, 16, 4; 557-561
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Conceptual design of blended wing body business jet aircraft
Autorzy:
Mulyanto, T.
Luthfi Imam Nurhakim, M.
Powiązania:
https://bibliotekanauki.pl/articles/242317.pdf
Data publikacji:
2013
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
transport
business jet aircraft
blended wing body
conceptual design
Opis:
Blended Wing Body concept offers several advantages compared to traditional aircraft tube and wing concept. The advantages mainly come from the distributed aerodynamic and structural loads, which leads to better aerodynamic performance as well as lighter structural weight. Most of the existing studies were focused on big transport aircraft carrying 400 to 800 passenger. In this study, a conceptual design of a business jet aircraft applying blended wing body concept is carried out. The market forecast for this category of aircraft can reach up to 24000 aircraft in the next 20 years. The possibility of having larger cross section is one of the competitive advantages, notably in a long-range flight. The requirement stated was to fly a trans-atlantic flight and carrying up to 18 passengers. It has to have a low floor height permitting easy passenger access. The design process consists of initial weight estimation, initial sizing, and preliminary aerodynamics, weight and balance and performance analysis. Some design consideration specially related with Blended Wing Body concept will be discussed, i.e. take-off and landing aerodynamics, structural concept, stability and control. The final design resulted in twin-engine aircraft, a Maximum Take-off Weight of 44 ton, cabin floor area of 6.9 x 10 m, winglet and split rudder for directional stability and control, and elevons for longitudinal and lateral control.
Źródło:
Journal of KONES; 2013, 20, 4; 299-306
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical Analysis of the Impact of Geometric Parameters of the Outcuts in the Wing Torsion Box Wall on the Mechanical Properties of the Structure
Autorzy:
Kopecki, Tomasz
Powiązania:
https://bibliotekanauki.pl/articles/2201747.pdf
Data publikacji:
2022
Wydawca:
Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:
outcut
advanced deformation
finite elements method
FEM
nonlinear analysis
wing torsion box
wing
aircraft construction
Opis:
The study presents the results of comprehensive numerical analyses of an unusual solution in the field of geometry of holes in the wall of the wing torsion box subjected to torsion. Due to the nature of loads acting on the wing structure in flight conditions, it is possible to modify the current standard solutions. However, this involves a fundamental change in the nature of stress distribution and the resulting need to use new types of local reinforcements of the structure. The analyses were supposed to indicate the dependencies between the geometric parameters of the outcuts and the nature of advanced deformations and the distribution of internal forces.
Źródło:
Advances in Science and Technology. Research Journal; 2022, 16, 3; 176--182
2299-8624
Pojawia się w:
Advances in Science and Technology. Research Journal
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Selected problems concerning the analysis of thin-walled structures with the use of finite element method
Autorzy:
Jachimowicz, J.
Mańkowski, J.
Osiński, J.
Powiązania:
https://bibliotekanauki.pl/articles/243328.pdf
Data publikacji:
2008
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
diagonal tension
wing structures
thin-walled structures
aircraft
FEM
modelling
Opis:
The aim of the paper was presentation and comparison of numerical methods applied in thin-walled structures analysis, with special attention paid to possibility of usage the Finite Element Method (FEM), especially in nonlinear analysis. There were presented basic differences between classical approach to modelling and analyzing thin-walled structures, and these performed with FEM methods using. The biggest emphasis was placed on the analysis of semimonocoąues, in which the loss in the shell 's stability is possible in the range of operational load activity. According to this, many nonlinear terms like global and local buckling, contact problems, significant deformations and shifts, are present. Worth emphasizing is the fact, that tension field, is something that was described long time ago. First paper s about this phenomenon were published in the last century. Although it is a common effect that takes place in semimonocoques, there are not many publications that analyze and examine this phenomenon. In this paper, an analysis of two-sided, thin-walled spar, which has undergone the flexion by the shearing force in the plane of the panel, was presented. The spar was designed as a classic semimonocoque, in which load transmission function is separated. It was assumed that, for the sake of small thickness, shell elements transmit mainly tangential loads, normal loads, when normal loads are transmitted by framework elements. Riveted joints are used to join elements of framework and shell. There are presented and compared results of analysis for models with various complexities. Firstly, results of analysis of classical model of semimonocoques were presented. It means that framework elements were modelled as rod elements transmitted only normal loads, but shell elements were modelled as disc semimonocoque elements, in this case transmitted only tangential loads. Area of section of rod elements was adequately increased, in order to consideration mating width, coming from partial transmission of normal loads by the shell elements. Results obtained for intermediate models were also presented, as well as for complex shell model, which allows on advanced nonlinear analysis of tension field, which consider contact between framework and shell elements. Applications of formulated models to thin-walled structure, especially aircraft ones and further possibilities of presented method of analysis were discussed.
Źródło:
Journal of KONES; 2008, 15, 1; 109-118
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical analysis and optimization of a winglet sweep angle and winglet tip chord for improvement of aircraft flight performance
Autorzy:
Al-Khafaji, Ali J. Dawood
Panatov, Gennady S.
Boldyrev, Anton S.
Powiązania:
https://bibliotekanauki.pl/articles/2096195.pdf
Data publikacji:
2022
Wydawca:
Polska Akademia Nauk. Polskie Towarzystwo Diagnostyki Technicznej PAN
Tematy:
lift
drag
lift coefficient
drag coefficient
aircraft wing
winglet
angle of attack
sweep angle
SOLIDWORKS
CFD
ANSYS FLUENT
współczynnik siły nośnej
współczynnik oporu
skrzydło samolotu
skrzydełko aerodynamiczne
kąt natarcia
SolidWorks
ANSYS Fluent
Opis:
In this paper, a study of the effect of winglet sweep angle and winglet tip chord of the aircraft wing on the aerodynamics performances and how to improve it are carried out, assuming Cant angle 60°, winglet height = 3.5 m, Toe angle = -5°, and Twist angle = +5°. Different sweep angles tested (-25°, -15°, 0°, +15°, +25°, +35°, and +45°) and winglet tip chord (0.25, 0.375, and 0.5 m). Four Angle of attack is presented (0°, 3°, 6°, and 9°). The aerodynamics properties of the wing were measured in terms of calculated lift to drag ratio to decide which wing has a high value of lift and lower drag. All models of a wing (eighty-four models) are drawn for 3D using the SOLIDWORKS program. Boeing 737-800 wing dimensions were used. All models of a wing were analyzed using ANSYS FLUENT. The results showed that sweep angle and winglet tip chord of the winglet by changing their configuration can improve aerodynamic performance for various attack angles. The maximum value of the lift to drag ratio was obtained with a sweep angle -15°, winglet tip chord 0.375m, and angle of attack 3°.
Źródło:
Diagnostyka; 2022, 23, 2; art. no. 2022210
1641-6414
2449-5220
Pojawia się w:
Diagnostyka
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Design and Optimisation of Fuel Tanks for BWB Configurations
Projektowanie i optymalizacja zespołu zbiorników paliwowych dla konfiguracji BWB
Autorzy:
Goraj, Z.
Powiązania:
https://bibliotekanauki.pl/articles/139593.pdf
Data publikacji:
2016
Wydawca:
Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:
blended wing body
BWB
aircraft design
fuel tank
aircraft structure
kadłub przechodzący płynnie w skrzydło
projekt statku powietrznego
zbiornik paliwa
konstrukcja statku
Opis:
This paper describes assumptions, goals, methods, results and conclusions related to fuel tank arrangement of a flying wing passenger airplane configuration. A short overview of various fuel tank systems in use today of different types of aircraft is treated as a starting point for designing a fuel tank system to be used on very large passenger airplanes. These systems may be used to move fuel around the aircraft to keep the centre of gravity within acceptable limits, to maintain pitch and lateral balance and stability. With increasing aircraft speed, the centre of lift moves aft, and for trimming the elevator or trimmer must be used thereby increasing aircraft drag. To avoid this, the centre of gravity can be shifted by pumping fuel from forward to aft tanks. The lesson learnt from this is applied to minimise trim drag by moving the fuel along the airplane. Such a task can be done within coming days if we know the minimum drag versus CG position and weight value. The main part of the paper is devoted to wing bending moment distribution. A number of arrangements of fuel in airplane tanks are investigated and a scenario of refuelling – minimising the root bending moments – is presented. These results were obtained under the assumption that aircraft is in long range flight (14 hours), CL is constant and equal to 0.279, Specific Fuel Consumption is also constant and that overall fuel consumption is equal to 20 tons per 1 hour. It was found that the average stress level in wing structure is lower if refuelling starts from fuel tanks located closer to longitudinal plane of symmetry. It can influence the rate of fatigue.
W pracy przedstawiono założenia, cele, metody, wyniki i wnioski dotyczące układu zbiorników paliwowych dla projektu samolotu pasażerskiego w konfiguracji BWB, t.j. kadłuba przechodzącego płynnie w skrzydło. Zamieszczono krótki przegląd współczesnych układów zbiorników paliwowych, które mogą stanowić punkt wyjściowy do projektu systemu paliwowego dla dużych samolotów pasażerskich. Takie systemy powinny umożliwiać przepompowywanie paliwa w celu zachowania położenia środka masy samolotu w akceptowalnych granicach, ze względu na warunki równowagi oraz stateczności samolotu. Wraz ze wzrostem prędkości środek parcia przesuwa się do tyłu samolotu i dla zachowania równowagi podłużnej zmianie ulega wychylenie sterów wysokości, trymera lub tzw. elewonów. Aby uniknąć nadmiernego wzrostu oporów wyważenia paliwo powinno być przepompowywane ze zbiorników położonych z przodu do zbiorników położonych w tylnej części samolotu. W tym celu obliczono zmianę oporu minimalnego w funkcji położenia środka masy i ciężaru samolotu. Główna część pracy jest poświęcona analizie rozkładu momentów gnących skrzydła w funkcji wypełnienia zbiorników paliwowych. Zbadano kilkanaście różnych wariantów wypompowywania paliwa ze zbiorników umieszczonych w skrzydle i zminimalizowano wartości momentów gnących u nasady skrzydła. Optymalizacje przeprowadzono przy założeniu, że samolot wykonuje długotrwały lot (14 godzin), ze współczynnikiem siły nośnej CL = 0:279 i przy stałym jednostkowym zużyciu paliwa (SFC = 20 ton na 1 godz = const). Stwierdzono, że średni poziom naprężeń w strukturze dźwigara głównego skrzydła jest najmniejszy jeżeli wypompowywanie paliwa rozpocznie się od zbiorników zlokalizowanych jak najbliżej pionowej płaszczyzny symetrii samolotu, czyli u nasady skrzydeł. Minimalizacja naprężeń może mieć istotny wpływ na zmniejszenie zmęczenia dźwigarów.
Źródło:
Archive of Mechanical Engineering; 2016, LXIII, 4; 605-617
0004-0738
Pojawia się w:
Archive of Mechanical Engineering
Dostawca treści:
Biblioteka Nauki
Artykuł
Wyświetlanie 1-15 z 16

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