Control of a nonlinear dynamic structural model of an F-15 tail section under primary resonance

Abstract

We used two simple control laws based on linear velocity and quantic feedback to suppress the high-amplitude vibrations of a structural dynamic model of the twin-tail assembly of an F-15 fighter when subjected to harmonic resonance excitations. We developed the nonlinear differential equations of motion and obtained an approximate solution using the method of multiple scales. Four first-order equations governing the amplitudes and phases of the response were derived. Then, a bifurcation analysis was conducted to examine the stability of the system and investigate the performance of the control laws. The theoretical findings indicate that the control laws lead to effective vibration suppression and bifurcation control. The results show that both laws are effective at suppressing the vibrations. To compare the performance of both techniques, we calculated the power requirements for a simple system.