A general interface method for aeroelastic analysis of aircraft
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A general interface method for aeroelastic analysis of aircraft

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Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

Subjects:

  • Aeroelasticity.,
  • Loads (Forces),
  • Mathematical models.,
  • Finite element method.,
  • Transformations (Mathematics),
  • Computational grids.,
  • Structural engineering.

Book details:

Edition Notes

Statementby T. Tzong ... [et al.].
SeriesNASA contractor report -- NASA CR-206331.
ContributionsTzong, T., United States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15491178M

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AIRCRAFT AEROELASTIC DESIGN AND ANALYSIS An introduction to fundamental concepts of static and dynamic aeroelasticity - with simple idealized models and mathematics to describe the essential features of aeroelastic problems. These notes are intended for the use of Purdue University students enrolled in AAE Flutter is a dynamic aeroelastic instability characterized by sustained oscillation of structure arising from interaction between those three forces acting on the body. The present work aims to study the flutter behavior on three-dimensional subsonic aircraft wings, using a computationally efficient Size: 2MB. Aeroelastic Dynamic Analysis of a Full F Configuration for Various Flight Conditions. Philippe Geuzaine, Applications of the unsteady vortex-lattice method in aircraft aeroelasticity and flight dynamics. Progress in Aerospace Sciences, Vol. Cited by: Chapter1: FundamentalsofAeroelasticAnalysis • IntroductiontoAeroelasticAnalysisandDesign • AerodynamicDataInputandGeneration • AerodynamicTheories.

Additionally, aeroelastic optimisation methods enable the potential of structural adjustments to, for instance, decrease mass and increase flight performance. In general, a new aircraft design concept or a part or system may cause new aeroelastic problems. A typical example is the whirl flutter phenomenon that is the subject of this book. on three-dimensional subsonic aircraft wings, using a computationally e cient method. For that, a computational aeroelasticity design framework is created using a custom devel-oped panel method for the uid ow analysis and a commercial software for the structural analysis. A validation of the ow solver is made using wind tunnel data, while the struc-File Size: 3MB. Flutter is a dynamic aeroelastic instability characterized by sustained oscillation of structure arising from interaction between those three forces acting on the body. The present work aims to study the utter behavior on three-dimensional subsonic aircraft wings, using a computationally e cient method.   Nonlinear Aeroelastic Analysis of Bending-Torsion Wings Subjected to a Transverse Follower Force 2 March | Journal of Computational and Nonlinear Dynamics, Vol. 6, No. 3 Stability and Open-Loop Dynamics of Very Flexible Aircraft Including Free-Wake EffectsCited by:

process, to develop methods for simplification of aircraft structural and aerodynamic models to make it possible to perform the load analysis in a fast and integrated way during conceptual and preliminary design phases, then to perform a load analysis of an ultralight aircraft as a case study for the demonstration of theFile Size: 2MB. The GSE/modal analysis method is applied to an aircraft analysis and design problem which involves computationally expensive CFD and CSM codes. High-fidelity static aeroelastic analysis is performed for a supersonic transport aircraft at Mach , g, cruise conditions, at an angle-of-attack, α, of °.Cited by: 6. Doublet Lattice Method- For the aeroelastic analysis, MSC/NASTRAN involves the doublet-lattice method for the subsonic aerodynamic calculation. The doublet-lattice method is used for the calculation of aerodynamic quantities in subsonic flow. This theory is a linearized potential-flow theory which is presented in references 6, 7, and 8. An aeroelastic stability analysis is presented for high-aspect ratio composite wings. The structural model is based on an asymptotically correct cross- sectional formulation and a nonlinear geometric ex- act beam analysis, both derivable from 3-D elastic- ity.