Design considerations for higher electrical power system voltages in aerospace vehicles

Cotton, Ian; Gardner, Richard; Schweickart, D.L.; Grosean, Dennis; Severns, Christopher

doi:10.1109/ipmhvc.2016.8012771

Cited by 21 publications

(10 citation statements)

References 5 publications

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“…Whilst this grounding topology offers fault ride through capability, the higher voltages on the unfaulted phases during a fault require that a higher level of voltage insulation is used [15]. The majority of faults in aircraft are caused by vibration and the resulting damage to cable insulation.…”

Section: Interdependencies Between Fault Response and Grounding mentioning

confidence: 99%

Grounding Topologies for Resilient, Integrated Composite Electrical Power Systems for Future Aircraft Applications

Jones

Sztykiel

Peña-Alzola

et al. 2019

AIAA Propulsion and Energy 2019 Forum

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The upwards trend for the use of electrical power on state of the art more-electric aircraft (MEA) has resulted in a significant changes to the electrical power system (EPS) for these platforms due to increased use of DC, higher voltage and power levels, and decentralized architectures. A dual trend is the increasing use of carbon fibre reinforced polymer (CFRP) for aircraft structures, due to the superior mechanical properties of CFRP compared to metallic structures. However, the poorer electrical conductivity of CFRP results in the aircraft structure no longer being fully integrated with the electrical power system. There is a need to integrate these two systems to fully maximize the performance benefits of CFRP, and optimize the weight and volume of the electrical power system. A first step in this integration is to identify an appropriate fault management strategy, which enables the detection of higher resistance ground faults through CFRP. This includes the consideration of appropriate grounding topologies. This paper proposes the implementation of a high resistance grounding topology, which enables the detection and location of a fault via spectral analysis of the voltage across the grounding resistor. From this, implications for wider EPS and CFRP designs to enable the reduction in the use of bulky cable harnesses, providing the first step to CFRP becoming an integral part of the EPS, are discussed.

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Section: Interdependencies Between Fault Response and Grounding mentioning

confidence: 99%

Grounding Topologies for Resilient, Integrated Composite Electrical Power Systems for Future Aircraft Applications

Jones

Sztykiel

Peña-Alzola

et al. 2019

AIAA Propulsion and Energy 2019 Forum

View full text Add to dashboard Cite

show abstract

“…The increase in the operating voltage of aircraft has been gradual, working both at the primary power system level as well as within aircraft subsystems (e.g., flight instruments, autopilot, electric flap gear motors, window heating, etc.). Electrical power systems for advanced aircraft employ voltages above the traditional levels of 12 to 42 VDC and 400 Hz [91]. Current airborne systems can contain 270 VDC, whereas bipolar systems with a 540 VDC differential are appearing in certain applications; moreover, some studies propose even a maximum operating voltage around 1500 V rms .…”

Section: Safety and High Voltage At High Altitudementioning

confidence: 99%

Review of High Power and High Voltage Electric Motors for Single-Aisle Regional Aircraft

et al. 2022

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This paper presents a review of the state of the art in electric propulsion for regional aircraft in the MW range. The implications surrounding the implementation of this technology, such as the need of high-power density or the use of high-voltage at high-altitude, are presented. Along with the challenges, the available technologies to face them are reviewed. Those are, as follows, the emerging new motor topologies for this purpose, the winding technologies, the materials employed for electric motors for aircraft propulsion and the ground-breaking use of high-temperature superconductors (HTS) as a high-power density enabler. Finally, a conclusion is presented gathering the main ideas of the paper.INDEX TERMS Aircraft propulsion, electric motor, high-power, high-temperature superconductor, high-voltage.

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“…For example, in an ungrounded (IT) grounding system, the EPS response to a rail to ground fault is a shift in the neutral voltage relative to ground, for both low and higher resistance faults [19]. Moreover, for a single line to ground fault, it allows for fault ride-through capability which may be particularly attractive for an aircraft EPS with critical loads [20]. However, due to capacitive connections to ground through parasitic connections (e.g., electrical machine casings) and common mode EMC filters, high transient over-voltages may occur during ground faults.…”

Section: Marinementioning

confidence: 99%

Electrical protection solutions enabling integrated electrical power and composite structure systems for aircraft

Preeti

Jones

Norman

et al. 2022

16th International Conference on Developments in Power System Protection (DPSP 2022)

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The combined dual trends for increased use of electrical power for more-electric aircraft (MEA) and carbon fibre reinforced polymer (CFRP) for light weight aircraft structures have been pursued to improve overall aircraft efficiency, reducing fuel burn and hence emissions. However, due to the poor electrical conductivity of CFRP, the CFRP structure and electrical power system (EPS) must be kept physically separate via bulky, heavy cable harnesses and raceways. The closer integration of EPS with CFRP structure offers an opportunity to optimize the weight and volume of the combined electrical power and structural systems, reducing the need for harnesses and raceways. To enable this, there is a need to understand the implications that this will have for electrical power systems design, including approaches to protection. This paper identifies candidate protection solutions for resilient, integrated electrical-composite aircraft structures, by consideration of the interdependent trades between MEA EPS architecture design, CFRP, grounding topology, and electrical fault response. The influence of these interdependent elements on protection requirements is explored, and as a result, design rules for the protection of such resilient, integrated systems are formulated and presented, enabling a focus on the fault response of the system and development of appropriate protection solutions.

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Design considerations for higher electrical power system voltages in aerospace vehicles

Cited by 21 publications

References 5 publications

Grounding Topologies for Resilient, Integrated Composite Electrical Power Systems for Future Aircraft Applications

Grounding Topologies for Resilient, Integrated Composite Electrical Power Systems for Future Aircraft Applications

Review of High Power and High Voltage Electric Motors for Single-Aisle Regional Aircraft

Electrical protection solutions enabling integrated electrical power and composite structure systems for aircraft

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