A dynamic model for stiffened composite multicell wing structures is developed. In this model, the extensional, bending, and coupling stiffnesses are calculated not only from the properties of the composite laminates of the wing skin but also from the stringers and spar flanges, which are treated as fibers of a pseudolamina. The arrangement of the wing spar webs and ribs is then treated like a sandwich honeycomb core, from which an equivalent transverse shear modulus of the wing structures is calculated. With these estimated properties, the composite wing structure is modeled, incorporating the effects of bending-torsion coupling, warping restraint, transverse shear deformation, shape of airfoil, rotary inertia, etc. To avoid complexity of formulation, the matrix form representation is introduced, which then makes most of the equations for the vibration analysis bear the same form as those of the classical beam theory. Thus, by following the classical approach, the composite wing structures can be studied analytically. To show the accuracy and generality of the comprehensive dynamic model for the vibration analysis of stiffened composite multi- cell wing structures, several illustrative examples are given, such as a bending-torsion coupled cantilever composite beam, a cantilever composite sandwich beam, and a NACA 2412 composite wing. Moreover, the influential factors on the natural frequencies, such as the transverse shear deformation, warping restraint, and shape of the airfoil are all studied by this unified and general formulation. An example for the forced vibration analysis is then given by the vibration suppression of a composite wing with piezoelectric sensors and actuators bonded on the wing surfaces, for which a linear quadratic Gaussian/loop transfer recovery (LQG/LTR) controller is designed and proved to be successful for vibration suppression of composite wings.
Vibration analysis of composite wing structures by a matrix form comprehensive model
Schwingungsanalyse einer Tragfläche aus Wabenstrukturlaminat mit einem auf Matrizenrechnung basierenden Modell
AIAA Journal ; 41 , 11 ; 2261-2273
2003
13 Seiten, 7 Bilder, 4 Tabellen, 30 Quellen
Article (Journal)
English
Biegeschwingung , Eigenfrequenz , Einspannung , erzwungene Schwingung , frei tragender Träger , LQR-Regler , mathematisches Modell , Matrizenrechnung , Modalanalyse , Modenkopplung , NACA-Profil , Regelungssimulation , Sandwich-Bauweise , Schermodul , Schubverformung , Schwingungsanalyse , Schwingungsbegrenzung , Schwingungsregelung , Steifigkeit , Torsionsschwingung , Tragfläche (Aerodynamik) , Verformungsart , Verwerfung (Verformung) , Wabenstrukturlaminat
Emerald Group Publishing | 2001