AEROELASTIC MODELING OF ACTIVE TWIST ROTORBLADES USING PARTICLE-WAKE AERODYNAMICS AND NON-LINEAR BEAM STRUCTURAL DYNAMICS

摘要

An overview of the initial development of SMARTROTOR ― a code for active aeroelastic aeroacoustic analysis of rotorcraft― is presented. SMARTROTOR interfaces a particle-wake panel method code with an active non-linear mixed variational intrinsic beam element code. In addition, a Ffowcs Williams-Hawkings equation-based acoustic component was developed for SMARTROTOR. The theory behind each component is reviewed. The method for aeroelastic coupling of the aerodynamic and structural components is presented. Sample acoustic results are presented for a model scale rotor. Sample aeroelastic results are presented for the NASA/ARMY/MIT Active Twist Rotor in hover. Future plans for SMARTROTOR, including acoustic and vibration studies, are discussed.