T-Tail Flutter Analysis with Simulated Fuselage Stiffness

Abstract

AbstractThe current work is a contribution to the potential effect of the aft fuselage stiffness modifications on the flutter characteristics of a T-tail. The rear fuselage is simulated by beam elements, based on a fixed T-tail structure. Their stiffness ranges from 1×105 N-m2 to infinite. The present analyses and discussion predict that a combination of out-of-plane or in-plane bending and torsion of the fuselage, fin, and stabilizer affects modes, and critical flutter and divergence speeds and flutter mechanisms, when the fuselage stiffness continuously varies. With the distinct segmental stiffness of the simulated fuselage, the different flutter results are compared and investigated. This paper also points out that the increasing joint stiffness of the stabilizer and fin can benefit the flutter characteristics. The calculated and analyzed database should be available to use for the structural design of the empennage in engineering