Design of an Electromagnetic Actuator for Rotorcraft Applications

FL Langley, PH Mellor

Research output: Chapter in Book/Report/Conference proceedingConference Contribution (Conference Proceeding)

Abstract

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 contributionDesign of an Electromagnetic Actuator for Rotorcraft Applications
Original languageEnglish
Title of host publicationACTUATOR 2006, 10th International Conference on New Actuators, Bremen, Germany, 14-16 June
Publication statusPublished - 2006

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