**7. Conclusions**

The matrix converter (MC) technology has been preferred since 1989 than other direct AC/AC converters or AC-DC-AC link converters because of its special features such as no DC link components, good sinusoidal input/output waveforms, inherent regeneration capability, and unrestricted output frequency. The published research work on the matrix converter focuses on the following ideas:


This novel research work is dedicated to matrix converter for more electric aircraft (MEA) application. And making MC suitable for aerospace applications by avoiding inherent regeneration in it, it means eliminating unique property of four-quadrant operation of MC, in order to satisfy the aircraft power quality specifications. Until this work, no one has paid attention on this research area, which will make the matrix converter feasible for aerospace applications and some specific industrial applications. For example, at the beginning of the twenty-first century, the matrix converter has been made as a commercial product, lift, which is manufactured by Yaskawa (Japan). The Power Electronics Machines and Control (PEMC) Group at the University of Nottingham has been developing 150-kVA matrix converter for higher power applications. Even though all three methods (BDS, IPC, and SCC) can produce good results, the standard clamp circuit method with power comparison technique is preferable because no auxiliary hardware is required. Hence, the weight, size, and cost of the matrix converter are considerably reduced. Therefore, the matrix converter with SCC method is recommended to aerospace applications where regeneration into the supply is not allowed. From

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**Author details**

provided the original work is properly cited.

Imayavaramban Munuswamy and Patrick W. Wheeler\*

\*Address all correspondence to: pat.wheeler@nottingham.ac.uk

*Matrix Converter for More Electric Aircraft DOI: http://dx.doi.org/10.5772/intechopen.81056*

their support to complete this research successfully.

such as more electric aircraft.

**Acknowledgements**

obtained experimental results, it is concluded that electrical braking with a matrix converter drive is feasible and matrix converter is opt for aerospace applications

The authors would like to thank Smiths Aerospace/GE Aviation laboratory for

© 2019 The Author(s). Licensee IntechOpen. This chapter is distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/ by/3.0), which permits unrestricted use, distribution, and reproduction in any medium,

School of EEE, University of Nottingham, Nottinghamshire, United Kingdom

obtained experimental results, it is concluded that electrical braking with a matrix converter drive is feasible and matrix converter is opt for aerospace applications such as more electric aircraft.
