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Structural and Aerodynamic Models in Nonlinear Flight Dynamics of Very Flexible Aircraft

Palacios, R, Murua, J and Cook, R (2010) Structural and Aerodynamic Models in Nonlinear Flight Dynamics of Very Flexible Aircraft AIAA Journal, 48 (11). 2648 - 2659. ISSN 0001-1452

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Abstract

An evaluation of computational models is carried out for flight dynamics simulations on low-speed aircraft with very-flexible high-aspect ratio wings. Structural dynamic models include displacement-based, strain-based, and intrinsic (first-order) geometrically-nonlinear composite beams, while thin-strip and vortex lattice methods are considered for the unsteady aerodynamics. It is first shown that all different beam finite element models (previously derived in the literature from different assumptions) can be consistently obtained from a single set of equations. This approach has been used to expand existing strain-based models to include shear effects. Comparisons are made in terms of numerical efficiency and simplicity of integration in flexible aircraft flight dynamics studies. On the structural modeling, it was found that intrinsic solutions can be several times faster than conventional ones for aircraft-type geometries. For the aerodynamic modeling, thin-strip models based on indicial airfoil response are found to perform well in situations dominated by small amplitude dynamics around large quasi-static wing deflections, while large-amplitude wing dynamics require three-dimensional descriptions (e.g. vortex lattice).

Item Type: Article
Additional Information: Copyright AIAA 2010 AIAA Journal, Vol. 48, No. 11 (2010), pp. 2648-2659 http://arc.aiaa.org/doi/abs/10.2514/1.J050513
Uncontrolled Keywords: Aeroelasticity, Flexible Aircraft, Geometrically nonlinear, Flight dynamics, Vortex lattice method, Beam
Divisions: Faculty of Engineering and Physical Sciences > Mechanical Engineering Sciences
Depositing User: Symplectic Elements
Date Deposited: 19 Nov 2012 14:39
Last Modified: 23 Sep 2013 19:37
URI: http://epubs.surrey.ac.uk/id/eprint/714249

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