Temat: wing aircraft - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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

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Skocz do pozycji: 2.

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

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Skocz do pozycji: 3.

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

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