A 20 KW matrix converter drive system for an electro-mechanical aircraft (EMA) actuator

Author

de Lillo, L. ; Empringham, L. ; Wheeler, P. ; Clare, J. ; Bradley, K.

Author_Institution

Power Electron. Machines & Control Group, Nottingham Univ.

fYear

2005

fDate

11-14 Sept. 2005

Abstract

This paper describes the design, construction and testing of a 20 KW matrix converter driven electromechanical actuator for an aircraft rudder demonstrator. The converter has been built using three custom designed modules each one containing a number of 600 V, 300 A IGBT´s and diodes sufficient to form a single output phase together with back to back diodes to detect the output current direction used in the commutation strategy. Practical results are shown. Description of the control structure, power circuit design, over voltage clamp circuit and practical results of the converter operating as an actuator position controller are presented

Keywords

aircraft; diodes; electric actuators; electric drives; insulated gate bipolar transistors; matrix convertors; position control; 20 kW; 300 A; 600 V; IGBT; actuator position controller; aircraft rudder demonstrator; commutation strategy; diodes; electromechanical aircraft actuators; matrix converter drive system; over voltage clamp circuit; power circuit design; Actuators; Aircraft manufacture; Circuit synthesis; Clamps; Diodes; Insulated gate bipolar transistors; Matrix converters; Phase detection; Testing; Voltage control; AC/AC Converter; Actuator; Aerospace; Matrix converter; Permanent magnet motor; Variable speed drive;

fLanguage

English

Publisher

ieee

Conference_Titel

Power Electronics and Applications, 2005 European Conference on

Conference_Location

Dresden

Print_ISBN

90-75815-09-3

Type

conf

DOI

10.1109/EPE.2005.219532

Filename

1665722