Technical Review of Dual Inverter Topologies for More Electric Aircraft Applications

Huang, Zujian; Yang, Tao; Giangrande, Paolo; Galea, Michael; Wheeler, Patrick

doi:10.1109/tte.2021.3113606

Cited by 42 publications

(15 citation statements)

References 113 publications

(253 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Reliability is a core requirement in electrical drive systems, especially in more electric aircraft and electric vehicles [3][4][5][6]. And the fault tolerant control of PMSMs has been intensively studied to improve the reliability.…”

Section: Nomenclaturementioning

confidence: 99%

Analysis and Fault-Tolerant Control for Dual-Three-Phase PMSM Based on Virtual Healthy Model

Zheng

Zou

et al. 2022

IEEE Trans. Power Electron.

View full text Add to dashboard Cite

Section: Nomenclaturementioning

confidence: 99%

Analysis and Fault-Tolerant Control for Dual-Three-Phase PMSM Based on Virtual Healthy Model

Zheng

Zou

et al. 2022

IEEE Trans. Power Electron.

View full text Add to dashboard Cite

“…Among RES that are explored for use on transportation systems [9–13], the Proton Exchange Membrane (PEM) fuel cells propulsion system is applicable to small UAV platforms up to 1.5 kW [14], with the fuel cell's specific energy density to range between 0.7 and 1 kWh/kg. This tends to increase up to 10 kWh/kg the next 10 to 15 years and up to 20 kWh/kg within 20 to 30 years, enabling the all‐electric flight of large aircraft [15].…”

Section: Introductionmentioning

confidence: 99%

A guide to unmanned aerial vehicles performance analysis—the MQ‐9 unmanned air vehicle case study

Zountouridou

Kiokes

Dimeas

et al. 2023

The Journal of Engineering

View full text Add to dashboard Cite

Great efforts are devoted for integrating Renewable Energy Sources (RES) on the propulsion system of Unmanned Air Vehicles (UAVs). This is applicable to small UAVs, having a horizon to expand to large UAVs within the next decades. For the conventional propulsion systems to be replaced, the required power needs of the aircraft should first be examined. The required power depends on the UAV's flight stage from takeoff to landing, whereas its calculation varies with regard to the propulsion system type, which is separated into two main categories, the propelled-driven engines and the jet engines. Two obstacles are arising. First, the parameters needed for the power estimation are commercially sensitive and second the analysis alters with respect to the engine's type. This paper focuses on the mathematical analysis of the required power for both the main propulsion systems, presented extensively for each flight phase, proposing, at the same time, a parameter estimation method which is applicable to any UAV type. The main purpose of this paper is to act as a guide for the calculation of any type UAV's required power at any flight stage. To validate the analysis, the MQ-9 Reaper/Predator B, a High Altitude Long Endurance (HALE) turboprop UAV produced by General Atomics is analysed. Its unknown parameters are estimated and based on a selected flight profile, the required power in terms of horsepower from takeoff to landing is assessed, for two scenarios regarding the aircraft's initial weight. In the first scenario the UAV has the maximum gross takeoff weight, whereas in the second scenario it does not carry any payload. The estimated required shaft power per flight phase for each scenario is then marked into the TPE331-10 turboprop engine characteristic curves.

show abstract

“…A comprehensive review of these strategies allows qualitative assessment of the performance of OW topologies. In [8], the OW drive topologies were reviewed considering the DC bus voltage utilization, output power quality, and fault-tolerant capability for aerospace applications. However, a comparative study among the existing control schemes is yet to be conducted.…”

Section: Introductionmentioning

confidence: 99%

“…However, a comparative study among the existing control schemes is yet to be conducted. The advantages of OW configuration over conventional Y-connected PMSM include multi-level operation, reduced converter capacity, more control flexibility due to a higher number of voltage vectors, and enhanced fault tolerance with the freedom to control each phase [7,8]. Compared to a 3-level multi-level converter, a dual converter system of OW configuration requires fewer capacitors than the flying capacitor multi-level converters, fewer isolated DC sources than H-bridge converters, and fewer diodes than the Neutral Point Clamped multi-level converters [9].…”

Section: Introductionmentioning

confidence: 99%

Open-Winding Permanent Magnet Synchronous Generator for Renewable Energy—A Review

et al. 2023

View full text Add to dashboard Cite

The open-winding permanent magnet synchronous machines (OW-PMSMs) have recently been gaining more attention because of their fault-tolerant capability and power quality comparable to a 3-level converter-driven system. This paper reviews the common configurations of OW-PMSM when used as a generator, highlighting its shortcomings and benefits. The OW-PMSM with a common DC bus was found to be a promising direct-drive generator solution for wind energy conversion (WEC) systems considering fault tolerance, DC bus utilization, and power quality when appropriate control algorithms are in place. The presence of the zero-sequence current is the key disadvantage of the common DC bus configuration. The review highlights the algorithms that have been proposed to suppress the zero-sequence current of the OW-PMSM under healthy and various fault conditions, especially the open-circuit fault of semiconductor switch. Shutting down remotely located wind turbines because of faults, until they can be repaired, may not make economic sense. The OW-PMSM can offer the opportunity, to run a WEC system even under fault conditions albeit with low output power. This paper will assess the literature gaps in the existing control techniques that prevent the extension via a comprehensive review.

show abstract

Technical Review of Dual Inverter Topologies for More Electric Aircraft Applications

Cited by 42 publications

References 113 publications

Analysis and Fault-Tolerant Control for Dual-Three-Phase PMSM Based on Virtual Healthy Model

Analysis and Fault-Tolerant Control for Dual-Three-Phase PMSM Based on Virtual Healthy Model

A guide to unmanned aerial vehicles performance analysis—the MQ‐9 unmanned air vehicle case study

Open-Winding Permanent Magnet Synchronous Generator for Renewable Energy—A Review

Contact Info

Product

Resources

About