Static Aeroelastic Response of Chiral-core Airfoils
نویسندگان
چکیده
منابع مشابه
Numerical and Experimental Analysis of the Static Compliance of Chiral Truss-core Airfoils
This paper presents an innovative wing profile featuring an internal truss-like structure of chiral topol-ogy. The chiral design is selected because of its unique deformation characteristics, which produce a theoretical, in-plane Poisson's ratio of −1. Such a Poisson's ratio yields a very high shear modulus, which in principle does not require the wing profile to be defined by a closed section ...
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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 ...
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Periodic cellular configurations with negative Poisson’s ratio have attracted the attention of several researchers because of their superior dynamic characteristics. Among the geometries with a negative Poisson’s ratio, the chiral topology features localized deformed configurations when excited at one of its natural frequencies. This is of particular importance as resonance can be exploited to ...
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STATIC aeroelastic analysis capability that calculates A flexible air loads for generic configuration wings was developed. It was made possible by integrating a finite element structural analysis code (MSWNASTRAN) and a panel code of aerodynamic analysis based on linear potential flow theory. The framework already built in MSC/NASTRAN was used, and the aerodynamic influence coefficient matrix w...
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The present paper addresses the aeroelastic optimization of a membrane wing. Aerodynamic optimization of a deforming wing has been done in recent work by Walker, Patil, and Canfield. The deformation shapes required for maximum thrust and thrust efficiency were calculated. In the present work, the maximum thrust for the membrane wing is calculated by optimizing the tension in the membrane so tha...
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ژورنال
عنوان ژورنال: Journal of Intelligent Material Systems and Structures
سال: 2007
ISSN: 1045-389X,1530-8138
DOI: 10.1177/1045389x06072361