Dynamics control of L-shaped composite structure in electric aircraft: Theoretical analysis and experimental validation

This paper focuses on the vibration control of an L-shaped composite structure, which is a simplified part of the motor support structure in an electric airplane. NiTiNOL steel wire rope (NiTi-ST) is employed as the vibration control mechanism. The study begins with a natural frequency and modal analysis using the Rayleigh-Ritz approach, which is subsequently validated using finite element analysis and experimental hammering methods. The dynamical equations are derived through the Lagrange method and then discretized using the Galerkin truncation method (GTM). Vibration responses of the simplified model are obtained through the harmonic balance method (HBM), and these results are confirmed through validation with the Runge-Kutta method (RKM). Based on the theoretical analysis, the experiments are carried out to optimize the vibration control scheme of L-shaped composite beam. The results demonstrates that the NiTi-ST wire rope effectively controls vibrations without affecting the system's natural frequency.