Computational/Experimental Aeroelastic Study for a Horizontal-Tail Model with Free Play

摘要

A computational code has been developed for aeroelastic analysis for an all-movable horizontal tail, and a companion wind-tunnel test program has been conducted. The structural bending and torsional stiffness are based upon an experimental tail model that has served as the basis for free-play design criteria. A linear three-dimensional time-domain vortex-lattice aerodynamic model is used to study the flutter and also nonlinear limit-cycle oscillations induced by a free-play gap in the actuating mechanism at the root of the tail as well as the effects of the root rotation angle (nominal angle of attack) on limit-cycle-oscillation response and gravity loads. It is found that the root rotation angle, gravity loads, and the initial conditions all significantly affect the limit-cycle-oscillation behavior. The computed aeroelastic responses are compared with the experimental data.