In this work, the aeroelastic stability behavior of composite hingeless rotor blade in forward flight is investigated by using the finite element method. The hingeless rotor model has soft-in-plane blade configurations and is Froud-scaled to match overall dynamic properties of full-scale helicopter rotors. The effects of transverse shear, torsion warping, and inplane elasticity are incorporated in the structural formulation. The shear correction factors capable of describing the coupling behavior of bending-shear and extension-shear are introduced here to consider the distribution of shear across the section of a composite blade. The aerodynamic model in the current aeroelastic analysis is formulated to allow either quasi-steady or unsteady two-dimensional aerodynamics. Compressibility and reversed flow effects on the blade are also incorporated. Numerical simulations are carried out to validate the current approach and to show the influence of elastic couplings on the aeroelastic stability solutions. The effects of unsteady aerodynamic models and geometric design variables such as precone, taper, and pretwist on the stability behavior of composite hingeless blade are also studied in detail.
Forward flight stability characteristics for composite hingeless rotors with refinned aeroelastic model
Stabilitätsverhalten im Horizontalflug von schwenkgelenklosen Verbundrotoren mit einem verbesserten aeroelastischen Modell
European Rotorcraft Forum, 23 ; 1 ; 9
1997
9 Seiten, 13 Bilder, 2 Tabellen, 16 Quellen
Conference paper
English
British Library Conference Proceedings | 1997
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