For the purpose of aeroelastic analysis of the Electrically Controlled Rotor(ECR)

an aeroelastic dynamic model is built in this paper.Firstly

a synthetic unsteady aerodynamic model in time domain is presented

which can take account of the unsteady effect of the flap nose overhang.The inertia effect of the flap is introduced into the structural dynamic model as an independent mass.According to the Hamilton principle

the nonlinear motion equation of the blade with flap is deduced with the form of generalized forces.Then

based on the finite element aeroelastic analysis code LORA01

the implicit equation of ECR blade motion is solved by an improved Newmark numerical integration method.At last

the ECR aeroelastic dynamic model is validated through comparison with the test results of the Active Control Flap(ACF) rotor.