**Acknowledgements**

*Aerospace Engineering*

**7. Conclusions**

**Figure 24.**

of MC

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

3.Addressing commutation techniques to avoid failure of the power circuit

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

research work on the matrix converter focuses on the following ideas:

1.MC for aerospace and industrial applications

*(a) During regeneration and (b) after avoiding regeneration.*

2.Power quality and stability of MC

4.Modulation topologies for the MC

**70**

The authors would like to thank Smiths Aerospace/GE Aviation laboratory for their support to complete this research successfully.
