1,721,025 research outputs found
Numerical-experimental comparison of graphite/epoxy panels with rectangular opening under uniaxial, biaxial and shear loading; Buckling load"
No full textAeroelastic response of 2-D lifting surfaces to gust and arbitrary explosive loading signatures
No full textAeroelastic response od a 2-D airfoil in a compressible flow field exposed to blast loading
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Critical Behaviour of Slender Wing Configurations
No full textThe next generation of slender, flexible aircraft wings requires extremely lightweight structures capable of carrying a considerableamountof non-structuralweight.With the increased slenderness and flexibility, possible with the advent of advanced composites, these wings can exhibit aeroelastic instabilities quite different from their rigid counterparts. The design of highly flexible aircraft, such as high-altitude long endurance (HALE) configurations, must include phenomena that are not usually considered in traditional aircraft design, such that an alternative design philosophy has been proposed for this class of vehicles. The discussion in this article is restricted, among the various aeroelastic phenomena, to the flutter condition. Classical procedures usually refer to aero-structural systems where the undeformedstate is taken as the reference point. This is not the case with slender wing configuration where, due to the high structural flexibility, a proper beam model, capable of describing the structural flight deflections, should be adopted. Consequently, the flutter analysis has to be performed considering the deflected state as a reference point. Herein, an approximate procedure is proposed and flutter is evaluated by means of Galerkin's approach applied to the perturbed small motions of the aero-structural system. The effect of typical parameters, including stiffness ratio, mass eccentricity, store pod, deflection amplitude, as well as the wing aspect ratio, are considered. For a simplified wing configuration, comparisons between analytical and experimental findings are presented along with discussions and suggestions for new design criteria. Keywords: advanced aircraft design, linear/non-linear aeroelasticity, flutter, experimental aeroelasticit
Unsteady aerodynamics in various flight speed regimes for flutter/dynamic response analyses, 18th
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Aeroelastic scaling laws with considerations to the design of an experimental slender wing model
No full textAirship Research and Development in the Areas of Design, Structures, Dynamics, and Energy Systems
No full textRecent years have seen an outpour of revived interest in the use of airships for a number of applications. Present day developments in materials, propulsion, solar panels, and energy storage systems and the need for a more eco-oriented approach to flight are increasing the curiosity in airships, as the series of new projects deployed in recent years show; moreover, the exploitation of the always mounting simulation capabilities in CAD/CAE, CFD and FEA provided by modern computers allow an accurate design useful to optimize and reduce the development time of these vehicles. The purpose of this contribution is to examine the different aspects of airship development with a review of current modeling techniques for airship dynamics and aerodynamics along with conceptual design and optimization techniques, structural design and manufacturing technologies and, energy system technologies. A brief history of airships is presented followed by an analysis of conventional and unconventional airships including current projects and conceptual designs
Implications of cubic physical/aerodynamic non-linearities on the character of the flutter instability boundary
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