Third method for regenerative braking in matrix converter drive: More electric aircraft

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.