NDLI: Numerical and Experimental Analysis of the Static and Dynamic Morphing Characteristics of a Chiral Core Airfoil

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Sapdoni, Alessandro Ruzzene, Massimo
Copyright Year	2006
Abstract	Aeroelastic tailoring requires structural compliance and thus often conflicts with stiffness requirements to carry prescribed aerodynamic loads. Recently, however, the application of cellular structural concepts has suggested the potential to achieve compliance while conserving required load-carrying capacity. Among the proposed concepts, a chiral geometry in particular is a novel configuration which features an in-plane negative Poisson's ratio which leads to a very high shear modulus, while maintaining some degree of compliance. In particular, the chiral geometry allows large continuous deformations of the airfoil assembly, with the constitutive material remaining in the linear region of its stress-strain curve. The ability to sustain large deformations without exceeding yield conditions is required to recover the original shape and to provide smooth deformations as required by aerodynamic considerations. In previous work, a coupled-physics model, comprising of simultaneous CFD and elastic analyses, is developed to investigate the influence of the chiral core geometry on the behavior of a given airfoil. The modification of geometric parameters defining the considered layout leads to significant variations in mechanical properties, which can be exploited to achieve various levels of compliance. The morphing capabilities of the proposed airfoil, quantified as camber changes, are evaluated for various design configurations of the internal core structure. Specifically, three such airfoils have been constructed to study the influence of core geometric parameters on the elastic behavior observed in numerical simulations. Experiments on the aforementioned airfoil samples are characterized by imposing large camber-wise deflections, via static loading, and measuring the resulting strain, both in the honeycomb core and in the airfoil profile. The experimental results confirm the ability of the airfoils to sustain large deflections while not exceeding yield strain limits, in addition to producing continuous deformations, which are critical for the implementation of aeroelastic tailoring.
Sponsorship	Materials Division, Nondestructive Evaluation Division, and Pressure Vessels and Piping Division
Starting Page	419
Ending Page	426
Page Count	8
File Format	PDF
ISBN	079184773X
DOI	10.1115/IMECE2006-15957
e-ISBN	0791837904
Volume Number	Materials, Nondestructive Evaluation, and Pressure Vessels and Piping
Conference Proceedings	ASME 2006 International Mechanical Engineering Congress and Exposition
Language	English
Publisher Date	2006-11-05
Publisher Place	Chicago, Illinois, USA
Access Restriction	Subscribed
Subject Keyword	Deformation Deflection Compliance Computational fluid dynamics Computer simulation Shear modulus Stress-strain curves Stress analysis (engineering) Elasticity Mechanical properties Airfoils Physics Stress Geometry Design Load bearing capacity Poisson ratio Experimental analysis Stiffness Manufacturing Shapes Honeycomb structures Elastic analysis
Content Type	Text
Resource Type	Article

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