Design of an Electromagnetic Actuator for Rotorcraft Applications

FL Langley; PH Mellor

Design of an Electromagnetic Actuator for Rotorcraft Applications

FL Langley
, PH Mellor

Research output: Chapter in Book/Report/Conference proceeding › Conference 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 contribution	Design of an Electromagnetic Actuator for Rotorcraft Applications
Original language	English
Title of host publication	ACTUATOR 2006, 10th International Conference on New Actuators, Bremen, Germany, 14-16 June
Publication status	Published - 2006

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@inproceedings{104b1b39d04147d4936b9bb156fd5ad4,

title = "Design of an Electromagnetic Actuator for Rotorcraft Applications",

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.",

author = "FL Langley and PH Mellor",

year = "2006",

language = "English",

booktitle = "ACTUATOR 2006, 10th International Conference on New Actuators, Bremen, Germany, 14-16 June",

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TY - GEN

T1 - Design of an Electromagnetic Actuator for Rotorcraft Applications

AU - Langley, FL

AU - Mellor, PH

PY - 2006

Y1 - 2006

N2 - 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.

AB - 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.

M3 - Conference Contribution (Conference Proceeding)

BT - ACTUATOR 2006, 10th International Conference on New Actuators, Bremen, Germany, 14-16 June

ER -

Design of an Electromagnetic Actuator for Rotorcraft Applications

Abstract

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