TY - JOUR
T1 - Multi-Domain Modeling and Simulation of High-Temperature Superconducting Transmission Lines under Short-Circuit Fault Conditions
AU - Podlaski, Meaghan
AU - Vanfretti, Luigi
AU - Khare, Abhijit
AU - Sumption, Michael
AU - Ansell, Phillip
N1 - Funding Information:
This work was supported in part by the National Aeronautics and Space Administration under Award 80NSSC19M0125, in part by the Center for High-Efficiency Electrical Technologies for Aircraft (CHEETA), in part by the Engineering Research Center Program of the National Science Foundation, in part by the Department of Energy under Award EEC-1041877, in part by the Center for Ultra-Wide-Area Resilient Electric Energy Transmission Networks (CURENT) Industry Partnership Program, and in part by the Center of Excellence for NEOM Research at the King Abdullah University of Science and Technology under Grant OSR-2019-CoE-NEOM-4178.12.
Publisher Copyright:
© 2015 IEEE.
PY - 2022/9/1
Y1 - 2022/9/1
N2 - Emission reduction in transportation requires advancements in aviation technologies enabling fully electrified propulsion, among which the use of superconducting technologies can provide untapped benefits given their low weight and minimal losses for high-power transmission. However, to enable their use in aircraft electrical power systems, additional considerations for electrical and thermal performance during faults is required in order to meet stringent aircraft safety requirements. In this work, a cryogenically cooled electric aircraft power system is studied under short-circuit conditions for different cooling media. This system consists of a fuel cell, high-temperature superconducting (HTS) transmission line, inverter, and motor, where each of their fault models have been explored. A trade-off study of the impedance of the fuel cell is conducted to identify the values at which the superconducting cable remains thermally stable after a short-circuit fault, as it is crucial that the cable does not experience a thermal runaway.
AB - Emission reduction in transportation requires advancements in aviation technologies enabling fully electrified propulsion, among which the use of superconducting technologies can provide untapped benefits given their low weight and minimal losses for high-power transmission. However, to enable their use in aircraft electrical power systems, additional considerations for electrical and thermal performance during faults is required in order to meet stringent aircraft safety requirements. In this work, a cryogenically cooled electric aircraft power system is studied under short-circuit conditions for different cooling media. This system consists of a fuel cell, high-temperature superconducting (HTS) transmission line, inverter, and motor, where each of their fault models have been explored. A trade-off study of the impedance of the fuel cell is conducted to identify the values at which the superconducting cable remains thermally stable after a short-circuit fault, as it is crucial that the cable does not experience a thermal runaway.
KW - Cryogenic cooling
KW - electrified aircraft modeling
KW - fault analysis
KW - liquid hydrogen
KW - superconducting lines
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U2 - 10.1109/TTE.2021.3131271
DO - 10.1109/TTE.2021.3131271
M3 - Article
AN - SCOPUS:85135771100
SN - 2332-7782
VL - 8
SP - 3859
EP - 3869
JO - IEEE Transactions on Transportation Electrification
JF - IEEE Transactions on Transportation Electrification
IS - 3
ER -