Abstract
A nonlinear flutter analysis is performed to study the limit-cycle-oscillation characteristics of an F-35 wind-tunnel model with horizontal-tail free-play effects using a direct simulation method. The result of this study is first validated with the wind-tunnel data. Then, a set of free-play design charts is generated to investigate the limit-cycle-oscillation-occurrence domain at various free-play angles and hinge moments of the horizontal tail. It is found that, as long as the horizontal tail is unloaded, the limit-cycle oscillation is inevitable even with a very small free-play angle. Furthermore, the free-play angle cannot be the only significant parameter involved in the free-play criteria. Therefore, it is suggested that an improved military specification for free-play limits of all-movable control surfaces be established. This effort will make a substantial impact on the control-surface design that may lead to a paradigm shift in the design criteria of aircraft structure.
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