Transverse shear behavior on the aeroelastic stability of composite rotor blades

Jung, Sung Nam; Kim, Seung Jo

doi:10.1007/bf02953939

KSME Journal

1996

DOI: 10.1007/bf02953939

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Transverse shear behavior on the aeroelastic stability of composite rotor blades

Sung Nam Jung

Seung Jo Kim

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Cited by 2 publications

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Aeroelastic stability analysis of hingeless rotor blades with composite flexures

Jung

Kim

2002

KSME International Journal

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The flap-lag-torsion coupled aeroelastic behavior of a hingeless rotor blade with composite flexures in hovering flight has been investigated by using the finite element method. The quasisteady strip theory with dynamic inflow effects is used to obtain the aerodynamic loads acting on the blade. The governing differential equations of motion undergoing moderately large displacements and rotations are derived using the Hamilton's principle. The flexures used in the present model are composed of two composite plates which are rigidly attached together. The lead-lag flexure is located inboard of the flap flexure. A mixed warping model that combines the St. Venant torsion and the Vlasov torsion is developed to describe the twist behavior of the composite flexure. Numerical simulations are carried out to correlate the present results with experimental test data and also to identify the effects of structural couplings of the composite flexures on the aeroelastic stability of the blade. The prediction results agree well with other experimental data. The effects of elastic couplings such as pitch-flap, pitch-lag, and flap-lag couplings on the stability behavior of the composite blades are also investigated.

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Aeroelastic stability analysis of hingeless rotor blades with composite flexures

Jung

Kim

2002

KSME International Journal

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Determination of the principal directions of composite helicopter rotor blades with arbitrary cross sections

Choi

et al. 2000

KSME International Journal

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Modern helicopter rotor blades with non-homogeneous cross sections, composed of anisotropic material, require highly sophisticated structural analysis because of various cross sectional geometry and material properties. They may be subjected by the combined axial, bending, and torsional loading, and the dynamic and static behaviors of rotor blades are seriously influenced by the structural coupling under rotating condition. To simplify the analysis procedure using one dimensional beam model, it is necessary to determine the principal coordinate of the rotor blade. In this study, a method for the determination of the principal coordinate including elastic and shear centers is presented, based upon continuum mechanics. The scheme is verified by comparing the results with confirmed experimental results.

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Transverse shear behavior on the aeroelastic stability of composite rotor blades

Cited by 2 publications

References 11 publications

Aeroelastic stability analysis of hingeless rotor blades with composite flexures

Aeroelastic stability analysis of hingeless rotor blades with composite flexures

Determination of the principal directions of composite helicopter rotor blades with arbitrary cross sections

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