Methods of modern aircraft aeroelastic analyses in the institute of aviation

• Autorzy: Chajec W.

Identyfikatory

DOI

10.5604/01.3001.0012.4773

• Języki publikacji: EN

Abstrakty

EN

The aeroelastic phenomena analysis methods used in the Institute of Aviation for aircraft, excluding helicopters, are presented in the article. In industrial practice, a typical approach to those analyses is a linear approach and flutter computation in the frequency domain based on normal modes, including rigid body modes and control system modes. They are determined by means of the finite element method (FEM) model of structure or a result of ground vibration test (GVT). In the GVT case, relatively great vibration amplitudes are applied for a good examination of a not truly linear structure. Instead or apart from the measure of generalized masses, a very theoretical model is used for mode shapes cross orthogonality inspection and improvement. The computed or measured normal mode sets are the basis for flutter analysis by means of several tools and methods, like MSC.Nastran and ZONA commercial software as well as our own low-cost software named JG2 for the flutter analysis of low speed aeroplanes and for a preliminary analyses of other aircraft. The differences between the methods lie in determining normal mode set, unsteady aerodynamic model, flutter equation formulation, time of analysis, costs, etc. Examples with results comparison obtained by means of distinguished methods are presented. Some works in the field of aeroelastic analysis with nonlinear unsteady aerodynamic in the time domain using Tau-code and ANSYS Fluent software were also performed. Aeroelastic properties of deformed structures, like a sailplane with deflected wings, can be also analysed. The simplest way of this analysis is the semi-linear approach in which the deflections modify the aircraft geometry for normal modes determination.

Słowa kluczowe

EN

flutter; normal modes; ground vibration test; unsteady aerodynamic model

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2018
• Tom: Vol. 25, No. 4
• Strony: 33--42
• Opis fizyczny: Bibliogr. 29 poz., rys.

Twórcy

autor

Chajec W.

• Institute of Aviation Materials and Structures Research Centre Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 251

Bibliografia

• [1] Chajec, W., MDM-1 Fox flutter analysis based on GVT, Mielec 1994.
• [2] Chajec, W., Seibert, T. Flutter calculation based on GVT-results and theoretical mass model, paper No. IFASD-2011-186 presented at the 15th International Forum on Aeroelasticity and Structural Dynamics, 26-30 June, Paris 2011.
• [3] Chajec, W., A Review of the methods of calculation analysis of flutter based on the I-23 aircraft, Transactions of the Institute of Aviation, No. 220, 2010.
• [4] Chajec, W., Aeroelastic Calculation of Innovative Non-conventional Aircraft with Swinging Canard Surface, paper No. IFASD-2013-11C presented at the 16th International Forum on Aeroelasticity and Structural Dynamics, 24-27 June, Bristol 2013.
• [5] Chajec, W., flutter computation based on ground vibration test results and mass data, Editor: Petrova, V. M., Advances in Engineering Research, 12, Ch. 5, Nova Science Publishers, Inc., 2016.
• [6] Chajec, W., Dziubiński, A., MSC.NASTRAN, ZONA ZAERO and ANSYS FLUENT flutter computation of rectangular wing with control surface – comparison with flutter wind tunel results, Transaction of Institute of Aviation, No. 2 (243), pp. 53-72, 2016, available at:http://ilot. edu.pl/prace_ilot/?spis_zeszytow/243_2016/5.html, 2016.
• [7] Chajec, W., Dziubiński, A., Modal approach in the fluid-structure interaction in aerospace, Advances in Mechanics: Theoretical, Computational and Interdisciplinary Issues. Proceedings of the 3rd Polish Congress of Mechanics (PCM) and 21st International Conference on Computer Methods in Mechanics (CMM), Gdansk, Poland, 8-11 September 2015, Taylor & Francis Ltd., 2015.
• [8] Chajec, W., Comparison of flutter calculation methods based on GVT results, paper No. 52, presented at session 7th EASN International Conf., available at: http://www.easn.net/documents/,Warsaw 2017.
• [9] Cieślak, S., Evaluation of the ground vibration test credibility, PhD dissertation, Institute of Aviation, Warsaw 2018.
• [10] Cieśliński, D., Data for flutter analysis in files ILR-33_FIN.nas (a FEM model) and ILR-33_flutter_parametry_lotu.xlsx (flight parameter for flutter analysis), 2018.
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• [14] Krzymień, W., Influence of structure static deflection on its proper vibration, Polish National MSC Software Users’ Conference, 1999.
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• [17] MSC Nastran, v.2012.1.0 , MSC.Software Corp., 2011.
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• [20] Nowak, M., Potkański, W., Flutter analysis of light aircraft methodology, Transactions of the Institute of Aviation, No. 65, 1976.
• [21] Stender, W., Kießling, F., Aeroelastic flutter prevention in gliders and small aircraft, DLR-Mitteilung 91-03, Göttingen 1991.
• [22] Strohmayer, A., Chajec, W., Krzymień, W., The effect of wing-tip propulsors on Icaré 2 aeroelasticity, three papers presented at session 2.3 of the 7th EASN International Conference, available at: http://www.easn.net/documents/, Warsaw 2017.
• [23] Rodden, W. P., Johnson, E. H., MSC NASTRAN Aeroelastic Analysis. User’s guide. Version 68, 1994.
• [24] Roszak, R., et al., Fluid structure interaction for symmetric manoeuvre base on ultra light plane, American Institute of Physics, Melville, New York 2011.
• [25] Wiśniowski, W., Ground vibration tests of flying objects – methods and results analysis, Transactions of the Institute of Aviation, No. 7 (209), 2010.
• [26] ZAERO Version 9.2 Theoretical Manual, ZONA Technology, Inc. 2017.
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• [28] Zboś, T., MDM-1 Fox wing stiffness and wing deflection line at n = 2, file wing-box & bend line.xlsx, 20.
• [29] ZEUS: ZONA’s Euler unsteady aerodynamic solver for aeroelastic applications, ZONA Technology, Inc. 2011.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).