An active control technique and wind tunnel test for gust load alleviation of a large-aspect-ratio flexible wing including geometric nonlinearities using trailing-edge control surface with servo which usually used in RC model is investigated. Nonlinear finite element method (FEM), nonlinear vortex lattice method (VI.M) and nonlinear double lattice method (DLM) is used for structural and aerodynamic modeling. State-space model is established in linearized system around large deformed state given after the nonlinear static aeroelastic analysis. Classic proportional-integral-derivative (PID) controller treats RC model servo as actuators and acceleration as the feedback signal. Method based on linearized system with large deformation can attach good agreement to wind tunnel test. Meanwhile, effectiveness of control technology is validated in test. The control system gives gust load alleviation (GLA) efficacy of vertical acceleration and root bending moment with the reduction rate being around 20%-40%.
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