**6. Experimental analysis**

The control platform includes both the control circuits and the interface circuits. The control circuit consists of a DSP card and an FPGA card as shown in **Figure 21**. The interface circuit includes encoder interface board and DSP daughter card (C6713DSK HPI), which is used to send user inputs and output waveforms plotting to troubleshoot hardware problems that are faced during hardware implementation and achieving desired output results. For example, if spike occurs while reversing the speed of the MC drive, the error data were captured and troubleshot through DSP daughter card. **Figure 22(a)** shows the RCC of three bidirectional switches (BDSAB, BDSBC, BDSAC) that are connected between MC input supply line voltages (VAB, VBC, VAC) and the small input filter capacitors (2).

**69**

**Figure 23.**

*Matrix Converter for More Electric Aircraft DOI: http://dx.doi.org/10.5772/intechopen.81056*

arrangement, respectively.

**Figure 22.**

dissipated through the RCC.

*(a) Torque, dq-currents and (b) stator currents of the motor.*

The RCC resistors (RAB, RBC, RAC) are connected in series (1) with the bidirectional switches. The triggering pulses (3) for bidirectional switches are obtained from FPGA card. **Figure 22(b)** shows complete experimental setup of MC drive. The host user interface PC is used to help monitor inputs to the system (complete experimental setup of MC drive) and get output from the system. The power circuit and control circuit of the laboratory prototype matrix converter drive is highlighted by letters (C) and (B), respectively. Letters (D) and (E) indicate the 4 kW induction motor with high inertial load and the RCC resistors with their heat sink

*(a) Photograph of RCC for BDS method and (b) complete experimental setup.*

Proof of BDS method for electrical braking in the MC drive by carried out experiments, at Smiths aerospace (later called GE Aviation) laboratory in PEMC Group of University of Nottingham, using a prototype rated at 7.5 kW MC fed a 4 kW IM. The field current (d-currents), torque current (q-currents), torque of IM and stator currents of IM during regeneration at speed reversal from +157 rad/s to −157 rad/s [Vin = 200 V, fs = 12.5 kHz, q = 0.75] are shown in **Figure 23(a)** and **Figure 23 (b)**, respectively. The input phase voltages (VA, VB), input phase currents (iA, iB), and three phase input power (using two-wattmeter method) during regeneration and after avoiding regeneration are shown in **Figure 24(a)** and **(b)**, respectively. The above experimental results (from **Figure 24(a)** and **(b)**) clearly show that the regenerative (negative) power is

**Figure 21.** *Layout of control and interface circuits.*

*Aerospace Engineering*

**6. Experimental analysis**

**Figure 20.**

The control platform includes both the control circuits and the interface circuits.

**Figure 21**. The interface circuit includes encoder interface board and DSP daughter card (C6713DSK HPI), which is used to send user inputs and output waveforms plotting to troubleshoot hardware problems that are faced during hardware implementation and achieving desired output results. For example, if spike occurs while reversing the speed of the MC drive, the error data were captured and troubleshot through DSP daughter card. **Figure 22(a)** shows the RCC of three bidirectional switches (BDSAB, BDSBC, BDSAC) that are connected between MC input supply line

The control circuit consists of a DSP card and an FPGA card as shown in

*Input phase powers for the SCC method with the IVR technique. Vin = 240 V, q = 0.75, and fs = 10 kHz.*

voltages (VAB, VBC, VAC) and the small input filter capacitors (2).

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**Figure 21.**

*Layout of control and interface circuits.*

**Figure 22.** *(a) Photograph of RCC for BDS method and (b) complete experimental setup.*

The RCC resistors (RAB, RBC, RAC) are connected in series (1) with the bidirectional switches. The triggering pulses (3) for bidirectional switches are obtained from FPGA card. **Figure 22(b)** shows complete experimental setup of MC drive. The host user interface PC is used to help monitor inputs to the system (complete experimental setup of MC drive) and get output from the system. The power circuit and control circuit of the laboratory prototype matrix converter drive is highlighted by letters (C) and (B), respectively. Letters (D) and (E) indicate the 4 kW induction motor with high inertial load and the RCC resistors with their heat sink arrangement, respectively.

Proof of BDS method for electrical braking in the MC drive by carried out experiments, at Smiths aerospace (later called GE Aviation) laboratory in PEMC Group of University of Nottingham, using a prototype rated at 7.5 kW MC fed a 4 kW IM. The field current (d-currents), torque current (q-currents), torque of IM and stator currents of IM during regeneration at speed reversal from +157 rad/s to −157 rad/s [Vin = 200 V, fs = 12.5 kHz, q = 0.75] are shown in **Figure 23(a)** and **Figure 23 (b)**, respectively. The input phase voltages (VA, VB), input phase currents (iA, iB), and three phase input power (using two-wattmeter method) during regeneration and after avoiding regeneration are shown in **Figure 24(a)** and **(b)**, respectively. The above experimental results (from **Figure 24(a)** and **(b)**) clearly show that the regenerative (negative) power is dissipated through the RCC.

**Figure 23.** *(a) Torque, dq-currents and (b) stator currents of the motor.*

**Figure 24.**

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