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.
高文杰 . 具有复合材料柔性梁的无轴承旋翼气动弹性稳定性[J]. , 2012, 31(22): 151-156.
Gao Wen-jie. AEROELASTIC STABILITY OF A BEARINGLESS ROTOR WITH A COMPOSITE FLEXBEAM IN HOVER. , 2012, 31(22): 151-156.