Effects of static aeroelasticity on composite wing characteristics under different flight attitudes

Abstract

Composite wing static aeroelasticity was analyzed through a loosely coupled method and the effects on composite wing characteristics under different flight attitudes were presented. Structural analysis and aerodynamic analysis were carried out through finite element method (FEM) software NASTRAN and computational fluid dynamics (CFD) software FLUENT, respectively. Correlative data transfer and mesh regenerate procedure were applied to couple the results of computational structure dynamics (CSD) and CFD. After static aeroelasticity analysis under different flight attitudes, it can be seen that lift increases with the increase of flight speed and the incremental value enlarges gradually in both rigid and elastic wings. Lift presents a linear increment relationship with the increase of attack angle when the flight speed is 0.4Ma or 0.6Ma, but nonlinear increment in elastic wing when flight speed is 0.8Ma. On the effect of aeroelasticity, the maximum of deformation increases with the increase of flight speed and attack angle, and the incremental value decreases with the increase of flight speed while uniform with different attack angles. The results provide a reference for engineering applications.

Keywords

static aeroelasticity / elastic deformation / aerodynamic characteristics / structural characteristics / flight attitudes

References

[1] PALACIOS R, CESNIK C. Static nonlinear aeroelasticity of flexible slender wings in compressible flow [J]. AIAA Paper, 2005, AIAA-2005-1945.

[2] AhremR., BeckertA., WendlandH.. Recovering rotations in aeroelasticity [J]. Journal of Fluids and Structures, 2007, 23(6): 874-884

[3] SvacekP.. Application of finite element method in aeroelasticity [J]. Journal of Computational and Applied Mathematics, 2008, 215(2): 586-594

[4] AttorniA., CavagnaL., QuarantaG.. Aircraft T-tail flutter predictions using computational fluid dynamics [J]. Journal of Fluids and Structures, 2011, 27(2): 161-174

[5] QinZ.Vibration and aeroelasticity of advanced aircraft wings modeled as thin-walled beams — dynamics, stability and control [D], 2001BlacksburgVirginia Polytechnic Institute and State University

[6] QinZ., LibrescuL.. Aeroelastic instability of aircraft wings modeled as anisotropic composite thin-walled beams in incompressible flow [J]. Journal of Fluids and Structures, 2003, 18(1): 43-61

[7] HaddadpourH., KouchakzadehM. A., ShadmehriF.. Aeroelastic instability of aircraft composite wings in an incompressible flow [J]. Composite Structures, 2008, 83(1): 93-99

[8] NaS., SongJ., ChooJ. H., QinZ.-ming.. Dynamic aeroelastic response and active control of composite thin-walled beam structures in compressible flow [J]. Journal of Sound and Vibration, 2011, 330(5): 4998-5013

[9] SmithM. J., HodgesD. H., CesnikC. E. S.. Evaluation of computational algorithms suitable for fluid-structure interactions [J]. Journal of Aircraft, 2000, 37(2): 282-294

[10] DowellE. H., HallK. C.. Modeling of fluid-structure interaction [J]. Annual Review of Fluid Mechanics, 2001, 33(1): 445-490

[11] CAI J, LIU F, TSAI H M. Static aero-elastic computation with a coupled CFD and CSD method [J]. AIAA Paper, 2001, AIAA-2001-0717.

[12] KamakotiR., ShyyW.. Fluid-structure interaction for aeroelastic applications [J]. Progress in Aerospace Sciences, 2004, 40(8): 535-558

[13] GURUSWAMY G. A new modular approach for tightly coupled fluid/structure analysis [J]. AIAA Paper, 2004, AIAA-2004-4547.

[14] DangH.-x., YangZ.-c., LiYi.. Accelerated loosely-coupled CFD/CSD method for nonlinear static aeroelasticity analysis [J]. Aerospace Science and Technology, 2010, 14(4): 250-258

[15] ShyyW., AonoH., ChimakurthiS. K.. Recent progress in flapping wing aerodynamic and aeroelasticity [J]. Progress in Aerospace Sciences, 2010, 46(7): 284-327

[16] DemasiL., LivneE.. Aeroelastic coupling of geometrically nonlinear structures and linear unsteady aerodynamics: Two formulations [J]. Journal of Fluids and Structures, 2009, 25(5): 918-935

[17] KAMAKOTI R, SHYY W. Moving grid computations for turbulent, aeroelastic flows [J]. AIAA Paper, 2003, AIAA-2003-3719.

[18] WONG A, TSAI H, CAI J, ZHU Y, LIU F. Unsteady flow calculations with a moving mesh algorithm [J]. AIAA Paper, 2000, AIAA-2000-1002.

[19] HuoS.-h., WangF.-s., YanW.-z., YueZ.-feng.. Layered elastic solid method for the generation of unstructured dynamic mesh [J]. Finite Element in Analysis and Design, 2010, 46(10): 949-955

[20] GouraG. S. L., BadcockK. J., WoodgateM. A.. A data exchange method for fluid-structure interaction problems [J]. Journal of Aircraft, 2001, 38(2): 282-342

[21] SADEGHI M, LIU F. Application of three-dimensional interfaces for data transfer in aero-elastic computations [J]. AIAA Paper, 2004, AIAA-2004-5376.

[22] JOSEPH A, GARCIA, GURU P G. Static aeroelastic characteristics of an advanced wing with a control surface using navier-stokes equations [J]. AIAA Paper, AIAA-1999-0796, 1999.

[23] MaT.-l., MaD.-l., ZhangHua.. Aerodynamic characteristic analysis of high-aspect ratio elastic wing [J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(7): 781-784

[24] ShiA.-m., YangY.-n., WangGang.. Investigations of characteristics of static aeroelasticity for elastic wing in transonic flow [J]. Engineering Mechanics, 2006, 23(5): 173-176

[25] ChenZ.-m., XuM., ChenS.-lu.. An analysis of structure response for transonic static aeroelasticity [J]. Journal of Air Force Engineering University, 2005, 6(1): 1-4