This paper describes the design and optimisation of an electromagnetic trailing edge flap actuator for active control of rotor-induced vibrations in a helicopter. Magnetostatic finite element analysis demonstrates that the actuator has a forceto-weight figure of 405N/kg, increasing to 445N/kg after design optimisation. Dynamic modelling confirms that the design is capable of operating at frequencies suited to multicyclic vibration control under the harshest aerodynamic loads.
|Translated title of the contribution||Design of an Electromagnetic Actuator for Rotorcraft Applications|
|Title of host publication||ACTUATOR 2006, 10th International Conference on New Actuators, Bremen, Germany, 14-16 June|
|Publication status||Published - 2006|