Abstract:
This paper describes a novel method for braking
regeneration in the Matrix Converter (MC) drive is proposed,
called Standard Clamp Circuit (SCC) method for More
Electric Aircraft (MEA). In earlier publications, Bi-Directional
Switch (BDS) method and Input Power Clamp (IPC) method
with Power Comparison (PC) technique and Input Voltage
Reference (IVR) technique for regenerative braking or
electrical braking in the Matrix Converter drive have been
discussed. The electrical braking is important in many
aerospace applications such as surface actuation and Air to Air
(in-flight) refueling system. Therefore, the inherent
regeneration capability of the Matrix Converter drive is not
desirable for aerospace applications so it has to be avoided. In
contrast to earlier methods, the proposed SCC method is using
the existing standard clamp circuit in the Matrix Converter
drive. The proposed methods are demonstrated through
detailed simulation results.
