Arcing fault in aircraft distribution network

Andrea, Jonathan; Buffo, Marc; Guillard, E.; Landfried, Romaric; Boukadoum, R.; Testé, Philippe

doi:10.1109/holm.2017.8088106

Cited by 18 publications

(18 citation statements)

References 7 publications

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“…More electric aircrafts (MEAs) allow for reducing weight [ 1 ], fuel consumption, greenhouse gas emissions, operation and maintenance costs and boosting overall system efficiency when compared with conventional aircrafts [ 2 ]. However, engineers are facing important challenges due to the increased voltage levels MEAs require, the increase in the power density and the d v /d t , or the reduction in distances between electrical wires, thus increase the likelihood of electric arc occurrence [ 3 , 4 ] with the consequent safety risks.…”

Section: Introductionmentioning

confidence: 99%

Corona Discharge Characteristics under Variable Frequency and Pressure Environments

Bas-Calopa

Riba

Moreno-Eguilaz

2021

Sensors

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More electric aircrafts (MEAs) are paving the path to all electric aircrafts (AEAs), which make a much more intensive use of electrical power than conventional aircrafts. Due to the strict weight requirements, both MEA and AEA systems require to increase the distribution voltage in order to limit the required electrical current. Under this paradigm new issues arise, in part due to the voltage rise and in part because of the harsh environments found in aircrafts systems, especially those related to low pressure and high-electric frequency operation. Increased voltage levels, high-operating frequencies, low-pressure environments and reduced distances between wires pose insulation systems at risk, so partial discharges (PDs) and electrical breakdown are more likely to occur. This paper performs an experimental analysis of the effect of low-pressure environments and high-operating frequencies on the visual corona voltage, since corona discharges occurrence is directly related to arc tracking and insulation degradation in wiring systems. To this end, a rod-to-plane electrode configuration is tested in the 20–100 kPa and 50–1000 Hz ranges, these ranges cover most aircraft applications, so that the corona extinction voltage is experimentally determined by using a low-cost high-resolution CMOS imaging sensor which is sensitive to the visible and near ultraviolet (UV) spectra. The imaging sensor locates the discharge points and the intensity of the discharge, offering simplicity and low-cost measurements with high sensitivity. Moreover, to assess the performance of such sensor, the discharges are also acquired by analyzing the leakage current using an inexpensive resistor and a fast oscilloscope. The experimental data presented in this paper can be useful in designing insulation systems for MEA and AEA applications.

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Section: Introductionmentioning

confidence: 99%

Corona Discharge Characteristics under Variable Frequency and Pressure Environments

Bas-Calopa

Riba

Moreno-Eguilaz

2021

Sensors

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“…AC generators could produce higher power output and were lighter-their power density was two times better. The weak arcing in the AC system did not cause significant problems [63]. Higher generated voltage level, 120 V, enabled the reduction of wires' crosssection.…”

Section: History Of Aircraft Electrical Systemsmentioning

confidence: 91%

Perspectives and Development of Electrical Systems in More Electric Aircraft

Arabul

Kurt

Arabul

et al. 2021

International Journal of Aerospace Engineering

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On-board electrical systems are the key components of each modern aircraft. They enable its safer, more comfortable, and environmentally friendlier operation. The strict regulations to reduce pollution and noise are produced by aircraft eventuated in projects like Clean Sky or ICAO Global Coalition for Sustainable Aviation. One solution to environmentally friendlier operation is the full electric propulsion of the aircraft, which enables the reduction of both noise and pollution. Such a concept requires a total change of all on-board power systems and enables the profound change in aircraft design. This paper presents the evolution of aircraft power systems into the so-called more electric aircraft (MEA) and discusses the state-of-the-art electrical systems. Furthermore, the concept of all-electric aircraft (AEA) is presented here.

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“…One important consideration to be made when choosing the individual components is the occurrence of electric arcing, due to isolation faults of ageing cables [37], for example. According to Paschen's law, at sea level pressure electric arcing can develop in air above voltages of 327 V. Reducing the pressure (i.e., by flying at a higher altitude than sea level) means that electric arcing becomes more critical [35].…”

Section: Power Electronics Sizingmentioning

confidence: 99%

Environmental life cycle assessment and operating cost analysis of a conceptual battery hybrid-electric transport aircraft

2021

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Noise and greenhouse gas emission targets set by e.g., the EU commission, NASA, and ICAO oblige the aviation industry to reduce its environmental footprint. Battery-powered hybrid-electric aircraft are currently being investigated in this regard as they can potentially reduce in-flight greenhouse gas emissions and noise. However, most studies to date have focused on the CO2 emission reduction potential instead of considering the total life cycle environmental impact. Hence, within this study an environmental life cycle assessment method for a hybrid-electric aircraft is developed and applied, supplemented by a direct operating costs analysis. This allows the simultaneous evaluation of the environmental impact reduction potential and the economic consequences for aircraft operators. This demonstrates the faced trade-off and contributes to a meaningful review process. A single-aisle transport aircraft (A320 class) serves as a use case for the established methodology. It consists of the conceptual aircraft design, the environmental life cycle assessment, and the direct operating costs analysis for a conventional reference aircraft and a hybrid-electric aircraft with a discrete parallel powertrain architecture. It should be noticed that the focus of this study is the comparison of conceptual aircraft designs of the same fidelity on system level, in lieu of the detailed modeling of a hybrid-electric aircraft. Results show that for a degree of hybridization of 0.3, the environmental impact of the hybrid-electric configuration increased by $$15.1\%$$ 15.1 % , while the operating costs increased by $$41.0\%$$ 41.0 % compared to a conventional reference aircraft. For a future scenario, favourable for hybrid-electric aircraft with i.a. renewable electricity production, the environmental impact could be reduced by $$7.0\%$$ 7.0 % compared to the reference aircraft. At the same time, the operating costs gap between both configurations decreases to $$+ 26.8\%$$ + 26.8 % . Hybrid-electric aircraft should therefore be investigated further as a potential solution to reduce the environmental impact of aviation, if simultaneously to developing them the expansion of renewable energies is fostered. Nevertheless, this reduction in environmental impact involves a high direct operating costs penalty.

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Arcing fault in aircraft distribution network

Cited by 18 publications

References 7 publications

Corona Discharge Characteristics under Variable Frequency and Pressure Environments

Corona Discharge Characteristics under Variable Frequency and Pressure Environments

Perspectives and Development of Electrical Systems in More Electric Aircraft

Environmental life cycle assessment and operating cost analysis of a conceptual battery hybrid-electric transport aircraft

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