Abstract
This article utilizes a nonlinear active vibration control to eliminate the helicopter blade flapping system oscillations having mixed excitation forces. The approximate solutions were calculated using the multiple scale perturbation technique. Furthermore, the stability and bifurcation analysis were investigated using the averaging method and Poincaré maps. In addition, numerical results exhibit the amplitude of the steady state against the detuning parameter and, the influences of all the parameters on the vibrating system behavior. Comparisons were carried out between analytical and numerical simulations to enclose the accuracy of our results. Finally, the current work is examined and compared to the published works.