Aeroelastic analysis of composite rotor blades in hover

✍ Scribed by Seong Min Jeon; Maeng Hyo Cho; In Lee

• Publisher: Elsevier Science
• Year: 1998
• Tongue: English
• Weight: 776 KB
• Volume: 66
• Category: Article
• ISSN: 0045-7949
• DOI: 10.1016/s0045-7949(97)00057-6

✦ Synopsis

The aeroelastic phenomena of a composite rotor blade in hover is investigated using a finite element method. A large deflection type beam theory is used for the one-dimensional global deformation analysis of the hingeless, isolated rotor undergoing arbitrary large displacements and rotations, but small strains. The sectional elastic constants of a composite box beam, including warping deformations, are determined from the refined cross-sectional finite element method. A two-dimensional, quasi-steady strip theory is applied for the aerodynamic calculation. Complete nonlinear equations are solved by the Newton-Raphson method to obtain an equilibrium position and the stability equations are linearized about this position. The modal approach method based on coupled rotating natural modes is u:led for the flutter analysis. The effects of fiber orientation and stacking sequences on the aeroelastic stability have been investigated. 0 1997 Elsevier Science Ltd Key wor&--Aeroelasticity, Box Beam, Composite blade, Hingeless rotor dynamics, Large deflection type beam theory A a0 B b c % D EI 13 E22> E33 etl, 62, 63