AEROELASTIC STABILITY OF A BEARINGLESS ROTOR WITH A COMPOSITE FLEXBEAM IN HOVER

Gao Wen-jie

Journal of Vibration and Shock ›› 2012, Vol. 31 ›› Issue (22) : 151-156.

PDF(1203 KB)
PDF(1203 KB)
Journal of Vibration and Shock ›› 2012, Vol. 31 ›› Issue (22) : 151-156.
论文

AEROELASTIC STABILITY OF A BEARINGLESS ROTOR WITH A COMPOSITE FLEXBEAM IN HOVER

  • Gao Wen-jie
Author information +
History +

Abstract

A new approach is presented to analysis aeroelastic stability of a bearingless composite rotor in hover. Nonlinear strain-displacement relations are presented using a large deflection beam theory which is modified from Bauchau’s beam mode. Assuming the stress components in the cross-section are equal to zero, constitutive relations for a composite blade are built. A new 24 degree-of-freedom finite element is developed for analysis and the finite element equations of motion for a blade are obtained from Hamilton’s principle. Aeroelastic stability of a bearingless rotor with a composite flexbeam in hover is investigated. Numerical results show that a negative ply angle stabilizes the first lag mode while a positive ply angle destabilizes the first lag mode. Eastic pitch-lag couplings caused by ply layup of flexbeam have significant effect on aeroelastic stability of a bearingless composite rotor. Negative pitch-lag coupling has a stabilizing effect on the lag mode damping. Positive pitch-lag coupling has a destabilizing effect on the lag mode damping. A reduction in ply thickness increases lag mode stability.

Key words

Nonlinear vibration / helicopter / bearingless rotor / composite flexbeam / aeroelasticity / hover / large deflection

Cite this article

Download Citations
Gao Wen-jie. AEROELASTIC STABILITY OF A BEARINGLESS ROTOR WITH A COMPOSITE FLEXBEAM IN HOVER[J]. Journal of Vibration and Shock, 2012, 31(22): 151-156
PDF(1203 KB)

1133

Accesses

0

Citation

Detail

Sections
Recommended

/