Review of More Electric Engines for Civil Aircraft

Liu, Yixiong; Mo, Da; Nalianda, Devaiah; Li, Yi-Guang; Roumeliotis, Ioannis

doi:10.1007/s42405-022-00469-0

Cited by 5 publications

(2 citation statements)

References 38 publications

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“…Based on the literature research, there are hydraulic, pneumatic, and electrical power structures as secondary power usage, especially in civil aircraft. However, current studies and market trends show that efforts to replace hydraulic and pneumatic systems with electrical power systems are gaining momentum [11]. The main reasons for this are the low efficiency of hydraulic systems, their long production and design processes, and the fact that they are more difficult to control than electrical systems.…”

Section: Introductionmentioning

confidence: 99%

Multilevel Aircraft-Inverter Design Based on Wavelet PWM for More Electric Aircraft

Catalbas,

Pakfiliz,

Soysal

2024

Energies

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This paper proposes a comprehensive power system designed for the use of a more electric aircraft power distribution system. Instead of traditional Nicad battery solutions as the energy source of the aircraft power system, lithium battery structures, which are a recent and promising solution in the field of aviation power systems, are modeled and analyzed. In this study, a WPWM-based, single-phase, multi-level pure sine wave static aircraft-inverter system is designed and integrated to improve the performance of conventional aircraft power systems. In the designed power system, a boost converter structure is proposed that boosts 28 VDC-to-270 VDC voltage coming from the lithium–ion battery pack and can reach a steady state in 0.032 s. The performance of the modeled WPWM-based aircraft-inverter system, compared to SPWM Bipolar and Unipolar switching techniques commonly used in single-phase inverter designs, reveals a THD reduction of approximately 27% with WPWM, resulting in a THD value below 2% for both load current and load voltage. As a result of the study, a power system that will enable the aircraft avionics, ventilation, and navigation systems to perform better than conventional power systems and comply with aircraft electric-power characteristic standards has been designed and detailed.

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Section: Introductionmentioning

confidence: 99%

Multilevel Aircraft-Inverter Design Based on Wavelet PWM for More Electric Aircraft

Catalbas,

Pakfiliz,

Soysal

2024

Energies

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“…The oil-immersed motor pump is a novel electro-hydraulic integrated power unit comprising an axial piston pump and a motor, exhibiting remarkable advantages of high efficiency, compact size, high energy utilization rate, high power density, and extended lifespan. It constitutes the essential component of the rudder control system for future large airliners and advanced warplanes, and represents a critical technology for the realization of intelligent actuation of high-end equipment [1][2][3]. However, due to its high-speed operation, it generates considerable heat within a limited time [3].…”

Section: Introductionmentioning

confidence: 99%

Thermal-Hydraulic Modeling of Oil-Immersed Motor Pump

Shi,

Li,

Gao

et al. 2023

Applied Sciences

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The integrated design of the motor and axial piston pump eliminates the coupling structure, resulting in a compact and lightweight motor-pump structure. The challenge of motors overheating has always been a major concern. To address this issue, the hydraulic oil throughout the motor pump is utilized for cooling the high-speed motor, effectively improving the power density and heat dissipation capability of the hydraulic power unit. This integrated design approach has successfully resolved the significant issue of overheating motors, leading to enhanced performance of the hydraulic power unit. To address this concern, the entire motor pump’s oil is utilized to cool the high-speed motor. Consequently, the thermodynamic prediction of high-speed motor pumps has become increasingly important. In this study, the impact of motor heat generation on hydrodynamics is analyzed, and the heat transfer of the motor pump is investigated using the control volume method. Furthermore, thermodynamic models of hysteresis loss, eddy current loss, alternating current loss, churning loss, and throttling loss are established for the oil-immersed motor pump. The change in oil viscosity is also considered. The instantaneous temperature change rule of the oil within the oil-immersed motor pump is derived. Additionally, the influence of various working conditions such as pressure and speed on the temperature of the motor pump’s key node is examined. The experimental results indicate the accuracy of the thermodynamic calculation, and the significant effect of motor loss on the leakage temperature.

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Development of flow metering for electric aircraft oil pump

Xuepeng,

Wenlong,

Yueming

et al. 2024

J. Phys.: Conf. Ser.

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In order to solve the difficulty of flow control in electric aircraft oil pump system, an electric aircraft oil pump was used as research object, with speed range of 2000rpm∼9000rpm, temperature range of 270K∼325K, pressure between the input and output of pump do not exceed 0.6MPa, and aviation 8B aircraft oil as medium. The influencing factors of aircraft oil flow were analysed, and an experimental system for researching flow metering methods was constructed. Based on the experimental data, an accurate flow metering model was established, which is significant for the metering and control of electric aircraft oil pump systems.

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Review of More Electric Engines for Civil Aircraft

Cited by 5 publications

References 38 publications

Multilevel Aircraft-Inverter Design Based on Wavelet PWM for More Electric Aircraft

Multilevel Aircraft-Inverter Design Based on Wavelet PWM for More Electric Aircraft

Thermal-Hydraulic Modeling of Oil-Immersed Motor Pump

Development of flow metering for electric aircraft oil pump

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