Modeling and identification of actuator for flap deflection

The electromechanical actuator (EMA) model is presented with the methods for identifying its design parameters. The actuator is a part of the system for flap deployment on the commercial transport airplane. The differential equations with the feedback control describe behaviour of the actuator deflection. There are two concepts of drive system simultaneously considered: a high torque/low speed (HT/LS) and a geared low torque/high speed (LT/HS). For parameter identification in both cases the Maximum Likelihood (ML) method with two minimisation algorithms: linearized Gauss-Newton and Levenberg-Marquardt is applied. Both approaches for each of two design solutions were effective, while tested on hypothetical data.