Research on Structural Response Modeling Method for Flutter Flight Test Under Sweep Excitation of Control Surface Based on Volterra Series

Sweep excitation of control surface is the most commonly used excitation method in flutter test flight. The Structural response under excitation has become the key analysis data in flutter test flight. Therefore, the modeling method of structural vibration response under sweep excitation of control surface in aircraft flutter test flight is studied, which can realize the prediction of structural vibration response and support flutter test flight. A modeling method of aeroelastic response based on Volterra kernel is proposed to realize the vibration response modeling of structure excited by sweep frequency of flutter test flight control surface. The Volterra kernel model of structural vibration response excited by sweep excitation of control surface is established. Based on the sweep excitation of control surface input and structural vibration response output, the Volterra kernel model of aircraft structural vibration response excited by sweep excitation of control surface is identified. The effectiveness of this method is verified by using the simulation data of pitching, sinking and floating aeroelastic system and aircraft flutter flight test data, which provides support for predicting the vibration response of structure excited by sweep excitation of control surface. The maximum peak error of the model response identified of the simulation system is 3.72%. The maximum peak error of flight test data identification model response is 5.65%.