关键词: 直升机, 旋翼, 气动弹性, 附翼, 振动

Abstract:

The aeroelastic analysis of a helicopter rotor blade with the controlled oscillating trailing edge flap is presented by building an aeroelastic model of the new concept rotor blade.The aerodynamic model with unsteady terms including the effect of the trailing edge flap has been used.The sensitivity of structural parameters of the trailing edge flap on vibration reduction is also studied.Numerical results show that significant reductions of vibratory vertical shears and hub moments in the fixed frame can be obtained for a four bladed soft inplane hingeless rotor.

Key words: helicop ter, ro to r, aeroelast icity, flap, vibrat ion