An aeroelastic model of a helicopter rotor

For the simulation of a flexible helicopter rotor system the Euler equations for a rotating and translating beam structure are derived using the Finite Element technique. Using the displacements and velocities of a beam element which has an airfoil shaped cross section the aerodynamic forces and moments are computed which form the loading of the elastic model. Using the Newmark integration method the transient response of the aerolastic model is solved.