Design and testing of electromechanical actuator for aerospace applications

Electromechanical actuators are gaining interest in the aerospace industry within the More Electrical Aircraft (MEA) architecture. The end-goal of fully electric aircraft includes Electromechanical actuation for flight control systems. The design and testing of a flight control system for helicopter swash-plate is presented in this work. The mechanical system is driven by electrical machines and controlled by dedicated power electronics, both of which fit challenging space requirements and environmental conditions. The predicted performances are validated by experimental testing of prototypes.

[1]  R I Jones,et al.  The more electric aircraft—assessing the benefits , 2002 .

[2]  Max Mulder,et al.  Aerodynamic Hinge Moment Coefficient Estimation Using Automatic Fly-by-Wire Control Inputs , 2009 .

[3]  M. Christmann.  INNOVATIVE APPROACHES TO ELECTROMECHANICAL FLIGHT CONTROL ACTUATORS AND SYSTEMS , 2010 .

[4]  C. Gerada,et al.  A computationally efficient design procedure for actuator motors using magnetic reluctance-and thermal resistance network models , 2012, 2012 XXth International Conference on Electrical Machines.

[5]  Wenping Cao,et al.  Overview of Electric Motor Technologies Used for More Electric Aircraft (MEA) , 2012, IEEE Transactions on Industrial Electronics.

[6]  C. Gerada,et al.  Analysis of a Closed-slot PM machine , 2013, 2013 International Electric Machines & Drives Conference.

[7]  Chris Gerada,et al.  Design optimisation of a fault-tolerant PM motor drive for an aerospace actuation application , 2014 .

[8]  David Gerada,et al.  A High-Speed Permanent-Magnet Machine for Fault-Tolerant Drivetrains , 2014, IEEE Transactions on Industrial Electronics.

[9]  Yong Shan,et al.  Effects of rotor downwash on exhaust plume flow and helicopter infrared signature , 2014 .

[10]  Craig Lawson,et al.  Electrical load-sizing methodology to aid conceptual and preliminary design of large commercial aircraft , 2015 .

[11]  Dimitri N. Mavris,et al.  An integrated approach to vehicle and subsystem sizing and analysis for novel subsystem architectures , 2016 .

[12]  Luca Papini,et al.  Fault Tolerant Design of Fractional Slot Winding Permanent Magnet Aerospace Actuator , 2016, IEEE Transactions on Transportation Electrification.

[13]  Marco Villani,et al.  PM brushless motor for helicopters electric tail rotor drive system , 2017, 2017 IEEE International Electric Machines and Drives Conference (IEMDC).