Nonlinear Aeroelastic Analysis of Control with Freeplay in Transonic Region

摘要

In this study an efficient aeroelastic analysis method was developed to deal with the aerodynamic nonlinearity caused by shock waves in the transonic region and the structural nonlinearity caused by freeplay. This method was then applied to a 3-D all-movable control wing to investigate, its nonlinear aeroelastic responses. The effects of the initial disturbance decreased in the transonic region compared with those in the subsonic region. As the size of the freeplay angle increased, the LCO amplitude increased and the nonlinear flutter velocity decreased in both the subsonic and transonic regions, which indicates degradation of the aeroelastic characteristics.