Modeling, simulation and analysis of a multi degree of freedom aircraft wing model
محورهای موضوعی : Applied MathematicsXueguang Bia 1 , Yucheng Liu 2
1 - Stanley Security Solutions, Inc., Shenzhen, Guangdong 518108, China
2 - Department of Mechanical Engineering, University of Louisiana, Lafayette, LA 70504, USA
کلید واژه: Freedom system, Force Determination Methods, Aircraft wing model,
چکیده مقاله :
This paper presented methods to determine the aerodynamic forces that acton an aircraft wing during flight. These methods are initially proposed for asimplified two degree-of-freedoms airfoil model and then are extensivelyapplied for a multi-degree-of-freedom airfoil system. Different airspeedconditions are considered in establishing such methods. The accuracy of thepresented methods is verified by comparing the estimated aerodynamic forceswith the actual values. A good agreement is achieved through the comparisonsand it is verified that the present methods can be used to correctly identify theaerodynamic forces acting on the aircraft wing models.
This paper presented methods to determine the aerodynamic forces that acton an aircraft wing during flight. These methods are initially proposed for asimplified two degree-of-freedoms airfoil model and then are extensivelyapplied for a multi-degree-of-freedom airfoil system. Different airspeedconditions are considered in establishing such methods. The accuracy of thepresented methods is verified by comparing the estimated aerodynamic forceswith the actual values. A good agreement is achieved through the comparisonsand it is verified that the present methods can be used to correctly identify theaerodynamic forces acting on the aircraft wing models.
[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.
