Modeling, simulation and analysis of a multi degree of freedom aircraft wing model

Theory of Approximation and Applications

مقاله 3، دوره 7، شماره 1، مرداد 2013، صفحه 21-62   

نوع مقاله: Research Articles

نویسندگان

Xueguang Bia^{* 1}؛ Yucheng Liu²

¹Stanley Security Solutions, Inc., Shenzhen, Guangdong 518108, China

²Department of Mechanical Engineering, University of Louisiana, Lafayette, LA 70504, USA

چکیده

This paper presented methods to determine the aerodynamic forces that act
on an aircraft wing during flight. These methods are initially proposed for a
simplified two degree-of-freedoms airfoil model and then are extensively
applied for a multi-degree-of-freedom airfoil system. Different airspeed
conditions are considered in establishing such methods. The accuracy of the
presented methods is verified by comparing the estimated aerodynamic forces
with the actual values. A good agreement is achieved through the comparisons
and it is verified that the present methods can be used to correctly identify the
aerodynamic forces acting on the aircraft wing models.

مراجع

[1] R. M. Kirby, Z. Yosibash, G.E. Karniadakis, “Towards stable coupling
methods for high order discretization of fluid-structure interaction:
Algorithms and observations”, Journal of Computational Physics, 223
(2), 2007, 489-518.
[2] F. Liu, J. Cai, Y. Zhu, H.M. Tsai, A.S.F. Wong, “Calculation of wing flutter
by a coupled fluid-structure method”, Journal of Aircraft, 38 (2), 2001,
334-342.
[3] J. A. Fabunmi, “Effects of structural modes on vibratory force
determination by the pseudoinverse technique”, AIAA Journal, 24 (3),
1986, 504-509.
[4] R. Kamakoti, Y. Lian, S. Regisford, A. Kurdila, W. Shyy, Computational
aeroelasticity using a pressure-based solver, AIAA-2002-869, AIAA
Aerospace Sciences Meeting and Exhibit, 40th, Reno, NV, Jan. 14-17,
2002.
[5] Y. Liu, W.S. Shepard, Jr., “Dynamic force identification based on enhanced
least squares and total least-squares schemes in the frequency domain”,
Journal of Sound and Vibration, 282(1/2), 2005, 37-60.
[6] E. Parloo, P. Verboven, P. Guillaume, M.V. Overmeire, “Force
identification by means of in-operation modal models”, Journal of Sound
and Vibration, 262 (1), 2003, 161-173.
[7] I. Lee, S.-H. Kim, “Aeroelastic analysis of a flexible control surface with
structural nonlinearity”, Journal of Aircraft, 32(4), 1995, 868-874.
[8] S. -H. Kim, I. Lee, “Aeroelastic analysis of a flexible airfoil with a freeplay
nonlinearity”, Journal of Sound and Vibration, 193 (4), 1996, 823-846.

[9] B. H. K. Lee, S.J. Price, Y.S. Wong, “Nonlinear aeroelastic analysis of
airfoils: bifurcation and chaos”, Progress in Aerospace Sciences, 35 (3),
1999, 205-334.
[10] I. D. Roy, W. Eversman, “Adaptive flutter suppression of an unswept
wing”, Journal of Aircraft, 33 (4), 1996, 775-783
[11] W. Eversman, I.D. Roy, “Adaptive flutter suppression using multiinput/
multi-output adaptive least mean square control”, Journal of
Aircraft, 34 (2), 1997, 244-250.
[12] G. Dimitriadis, J. E. Cooper, “A method for identification of non-linear
multi-degree-of-freedom systems”, Proceedings of the Institution of
Mechanical Engineers, Part G: Journal of Aerospace Engineering, 212
(4), 1998, 287-298.