Avoiding regeneration with a matrix converter drive

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

Avoiding regeneration with a matrix converter drive

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

Matrix Converter for More Electric Aircraft

This proposed chapter discusses three methods that do not allow regenerative power from the matrix converter (MC) motor drive onto the aircraft power supply. According to aerospace power quality specifications, the regenerative power must be dissipated in the drive itself to avoid instability problem in aircraft power supply. These are bidirectional switch (BDS) method, input power clamp (IPC) method, and standard clamp circuit (SCC) method for aerospace applications. To identify regeneration in a matrix converter drive, two novel techniques are proposed. These are power comparison technique (PC) and input voltage reference technique (IVR). In both techniques, output power of MC and direction of speed, these factors are used to detect regeneration in MC drive. 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. The proposed methods are demonstrated through detailed simulation results and experimental verification. In order to prove the proposed methods with novel techniques, a 7.5-kW matrix converter fed 4-kW induction motor (IM) with inertial load has experimentally implemented. The obtained results using BDS method with PC technique proved avoiding regeneration with a matrix converter is feasible. This chapter is valuable for 150-kVA matrix converter for high-power application

Electrical braking in matrix converter for more electric aircraft: bi-directional switch and input power clamp methods

Current aircraft power quality specifications do not allow regeneration onto the power bus. Therefore, the inherent regeneration available from Matrix Converter (MC) is not desirable in More Electric Aircraft (MEA) aerospace applications. In this paper, novel methods to avoid regeneration from the Matrix Converters are proposed. The methods have been called the Bi-Directional Switch (BDS) method and the Input Power Clamp (IPC) method. Both methods are compared. The IPC method is considered an alternative to the Bi-Directional Switch (BDS) method and has a number of advantages discussed in the paper. To detect regeneration in Matrix Converters two techniques are proposed, the Power Comparison technique (PC) and the Input Voltage Reference technique (IVR). Experimental results from a prototype using 4 kW Induction Motor are presented

Standard clamp 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