Identification and assessment of a nonlinear dynamic actuator model for controlling an experimental flexible wing

Abstract In this paper, the effect of nonlinear actuator dynamics on performance an active load alleviation system for experimental flexible wing is studied. Common nonlinearities such as backlash or rate limits are considered control surface actuator. An aeroelastic simulation model a with being used. With this, parameter study carried out to quantify impact individual overall closed-loop by means describing functions. Finally, parameters identified from dedicated tests experimentally validated allowing accurate prediction expected gust performance.