Recently, the conventional Matrix Converter has been considered for aerospace applications because of its compactness in weight and size due to absence of a DC-Link capacitor. In addition the Matrix Converter is capable of producing a variable output voltage with unrestricted input and output frequency. This is useful in aerospace applications which require a wide range of input frequency, sometimes from 360 Hz to 900 Hz. These key features are only obtained from the Matrix Converter without using any large passive components. The Matrix Converter has an inherent regeneration capability. However, the avoidance of the regeneration may be vital in many aerospace applications, such as aircraft surface actuation systems. According to current aircraft power quality specifications regeneration is not allowed and must be dissipated with in the Matrix Converter drive itself.
This thesis proposes two novel methods which allow regeneration from the Matrix Converter motor drive to be avoided. These are the Bi-Directional Switch (BDS) method and Input Power Clamp (IPC) method. In order to detect regeneration in the Matrix Converter motor drive two techniques are used. These are the Power Comparison (PC) technique and Input Voltage Reference (IVR) technique. Finally, to validate the proposed methods a Matrix Converter has been designed and built with a Regeneration Control Circuit (RCC). Indirect vector control is used to control 4.0 kW Induction Motor. Based on the simulation results and experimental results using the BDS method to avoid regeneration with a Matrix Converter is feasible
