Flutter analysis of a general wing is carried out using finite element structural modeling (MSC/NASTRAN), a subsonic kernel function unsteady aerodynamics and a V-g type of solution (FAST). The shape of the wing cross section is generated by parameterization using the Joukowski transformation, so that shapes of varying thickness and camber can be obtained by varying the parameters. The CQUAD4 (quadrilateral) and CTRIA3 (triangular) membrane-bending shell elements, the CBAR beam element and the CSHEAR shear panel element from MSC/NASTRAN have been used in this study. The validation of finite element modeling is done by performing dynamic analysis of an Agard swept wing model. The sensitivity of flutter speed of the wing to shape parameters, namely aspect ratio, area, taper ratio, and sweep angle is obtained using a central difference scheme in conjunction with automatic differentiation (ADIFOR). The sensitivity of flutter speed to modal parameters, namely, natural frequency, generalized mass, and generalized aerodynamic forces is computed using ADIFOR.
Aeroelastic sensitivity analysis of wings using automatic differentiation
Aeroelastische Sensitivitätsanalyse von Tragflügeln unter Anwendung der automatischen Differenzierung
AIAA Journal ; 35 , 3 ; 519-525
1997
7 Seiten, 13 Bilder, 2 Tabellen, 8 Quellen
Aufsatz (Zeitschrift)
Englisch
Finite-Elemente-Methode , Flatterschwingung , konforme Abbildung , Tragflügel , geometrische Form , Programmpaket , Simulationsprogramm , Biegebeanspruchung , Schale (Flächentragwerk) , Scherbeanspruchung , Pfeilflügel , Modalparameter , Differenzenverfahren , Eigenfrequenz , Masse (physikalische Größe) , Empfindlichkeit
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