Optimal Voltage for More Electric Aircraft direct current cabling system

Recalde, Angel A.; Bozhko, Serhiy; Atkin, Jason; Sumsurroah, Sharmila

doi:10.1109/itec51675.2021.9490090

Cited by 4 publications

(5 citation statements)

References 12 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This system has lowest reliability if some of the FCs degrade or in the case of faults. This configuration at high voltage (>3000V [18]) is not recommended due to lack of protections and insulation designed for partial discharges at high altitude (at 40kft of altitude above sea level) that can be used without high weight penalties. (b -b) 8 stacks can be connected in series.…”

Section: Configurations Descriptionmentioning

confidence: 99%

“…Efficiency optimization with only few power electronics converters. This configuration at high voltage (>3000V [18]) is not recommended due to partial discharges at high altitude. However, if the design of cable insulation changes to provide higher power density, higher voltages can be recommended.…”

Section: Configurations Descriptionmentioning

confidence: 99%

“…In this paper we have selected a fixed 2000V DC-bus voltage as a system voltage and a variable DC-bus voltage up to 3080V. Both voltages are below the threshold studied in [18] for operating at a safe voltage at high altitude for regional aircraft.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

The Impact of Multi-Stack Fuel Cell Configurations on Electrical Architecture for a Zero Emission Regional Aircraft

Zaghari

Zhou

Enalou

et al. 2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

All-electric aircraft can eliminate greenhouse gas emissions during aircraft mission, but the low predicted energy storage density of batteries (=0.5 kWh/kg), and their life cycle, limits aircraft payload and range for regional aircraft. Proton Exchange Membrane Fuel Cells (PEMFCs) using hydrogen are explored as an alternative power source. As the effort on designing high power density and highly efficient fuel cell systems continues, a trade off study on the effect of fuel cell configurations and the electrical conversion strategy on system efficiency, total weight, failure cases, and reduction of power due to failures, will inform future designs. Introducing viable fuel cell stacks and electrical configurations motivates such a trade off study, as well as concentrated design effort into these components. Currently available fuel cell stacks are designed at lower power (in the range of 150kW) to what is required for regional aircraft propulsion (in the range of 4MW). Hence to achieve the total required power, the fuel cell stacks are connected in parallel and series to create multi-stack configurations and provide higher power. In this study, multi-stack fuel cell configurations and the selected DC/DC converters are assessed. Each configuration is evaluated based on power converter design and redundancy, design for high voltage, degradation of fuel cell stacks, total system efficiency, and controllability of fuel cell stacks.

show abstract

Section: Configurations Descriptionmentioning

confidence: 99%

Section: Configurations Descriptionmentioning

confidence: 99%

See 1 more Smart Citation

The Impact of Multi-Stack Fuel Cell Configurations on Electrical Architecture for a Zero Emission Regional Aircraft

Zaghari

Zhou

Enalou

et al. 2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

show abstract

“…In the design of MEA, finite element analysis (FEA) simulation is also used to calculate the electric field distribution, which can effectively indicate the probability of PD. Aiming at the simple model where the cable is located at a fixed distance from the ground (infinite plane, as shown in Figure 12), the optimal withstand voltage with regard to the cable with different sizes and insulation materials can be obtained by theoretical calculation [97]. In which, D represents the distance between the conductor centre and the ground; e is the distance between the outer insulation layer of the cable and the ground.…”

Section: Insulation Challenges For More‐electric Aircraftmentioning

confidence: 99%

A review on insulation challenges towards electrification of aircraft

Jiang

et al. 2023

High Voltage

View full text Add to dashboard Cite

Compared to the traditional aircraft, electrification of power system in aircraft has potential to revolutionise the aviation industry. Typically, more-electric aircraft (MEA), even all-electric aircraft has been developed and delivered to decrease the greenhouse gas emission and increase the energy efficiency. The next generation of MEA will operate at high voltage to facilitate the transfer of significant levels of electrical power in an electrified aircraft. However, the higher voltage inevitably leads to an increased risk to the insulation of the electrical components and power system. This study aims to provide a critical overview of the insulation challenges from the perspective of electrified aircraft, typically MEA application. The development of MEA and the special working conditions are explained at the beginning. Then the insulation challenges of power modules, electric machines, aeronautical cables etc. are discussed in detail. Finally, the existing technical barriers and future prospects of insulation for electrified aircraft are summarised. It provides a reference for the future design and test in power system of next generation MEA and related electrified air transportations.

show abstract

“…A fixed 2000V DC-bus voltage was selected as a system voltage below the 3000V voltage threshold identified in [30] for operating at a safe voltage at high altitude for regional aircraft. In a study conducted by Vratny et al [31], for a constant system voltage architecture in a 6MW powertrain optimum system, the voltage was identified at higher voltages, between 3000V and 4000V.…”

Section: Fig 4 Conceptual Schematic Of the 8-propeller Fc Aircraftmentioning

confidence: 99%

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

Pontika

Zaghari

Zhou

et al. 2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

This paper presents the development and application of an integrated, higher-fidelity framework developed within CHARM (the Cranfield Hybrid electric Aircraft Model) for the design, performance analysis and overall evaluation of novel electrified propulsion systems. The developed framework is used to model and analyze the performance characteristics of a Fuel Cell (FC) regional aircraft system in comparison with a conventional regional aircraft and a hydrogen gas turbine regional aircraft retrofit. The FC propulsion system and the hydrogen gas turbine are retrofitted to the same conventional aircraft platform. Physics-based aircraft performance calculations, propeller maps, gas turbine component maps, off-design cycle analysis, electric component maps, calculations for the electric power management and distribution, and a Proton-Exchange Membrane FC (PEMFC) configuration sized to cover the power requirements of a regional aircraft, are integrated within this framework to capture the performance and interaction of components, sub-systems and aircraft during any flight mission and conditions. The aircraft performance, the propulsion system performance characteristics and the emissions of the three technologies are calculated and discussed to understand the challenges and opportunities of using hydrogen-electric propulsion (FC). The effect of capturing the variable mission parameters and flight phases on the performance of the electric power system and FC is presented and compared against a lower fidelity modeling approach for the electric powertrain. The sensitivity of the FC propulsion system and its attributes to varying mission requirements (island-hopping, range, cruise altitude, ambient conditions), as well as the change in the consumed fuel, are demonstrated. This framework can be used to inform the decision-making for the design of electric components and thermal management systems (TMS), and the importance of capturing the trade-off between mass, efficiency and operational constraints in the design process is highlighted. Also, the off-design performance of the electric power system designs and FC is modeled to decide if the design is within acceptable limits under various conditions, and capture the effect of mission requirements and flight conditions on the energy consumption of the overall aircraft system. Finally, a parametric analysis addresses the effect of power density improvement with future technology on the energy per passenger and feasibility of the FC regional aircraft.

show abstract

Optimal Voltage for More Electric Aircraft direct current cabling system

Cited by 4 publications

References 12 publications

The Impact of Multi-Stack Fuel Cell Configurations on Electrical Architecture for a Zero Emission Regional Aircraft

The Impact of Multi-Stack Fuel Cell Configurations on Electrical Architecture for a Zero Emission Regional Aircraft

A review on insulation challenges towards electrification of aircraft

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

Contact Info

Product

Resources

About