Comparison and Analysis of Multi-State Reliability of Fault-Tolerant Inverter Topologies for the Electric Aircraft Propulsion System

Cao, Yongtao; Fauth, Leon; Mertens, Axel; Friebe, Jens

doi:10.23919/icems52562.2021.9634654

Cited by 7 publications

(4 citation statements)

References 15 publications

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“…Additionally, special fault-tolerant operation schemes can be applied. Important research topics are therefore reliability and fault tolerance of inverter [49]. The tight integration of inverter and motor as assumed here is an important measure for minimizing or fully neglecting output filter requirements.…”

Section: Discussionmentioning

confidence: 99%

“…The reliability of power electronic systems can be further improved, if fault-tolerant operation strategies can be utilized. For example, three-level ANPC or NPC inverter can still provide full performance or reduced performance under several fault scenarios with adequate fault-tolerant operation strategies [49]. Such kind of fault-tolerance is especially helpful if a critical failure occurs at take-off phase, where maximal power is required.…”

Section: Safety Consideration For Power Electronic Systemmentioning

confidence: 99%

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Power Distribution and Propulsion System for an All-Electric Short-Range Commuter Aircraft—A Case Study

et al. 2022

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To participate in the transition towards a sustainable use of energy, the aircraft sector needs to be transformed with respect to the energy carrier and propulsion methods. For smaller aircraft, a battery-electric approach is promising. While this will require extensive research and design as well as the application of advanced components which are partly not available to this date, general design rules and decisive parameters and components can already by deduced. This publication presents the exemplary design of the full propulsion system for a small commuter aircraft. This serves as a case study to highlight the influence of components and parameters on the overall efficiency and weight of the system. By that, future research can be directed towards the areas of high impact on the realization of all electric aircraft.INDEX TERMS Aviation, aerospace electronics, AEA, aircraft propulsion, DC/DC converters, electric power supply systems, high voltage direct current, power semiconductor devices, reliability, safety, wide bandgap semiconductors, wiring harness Nomenclature This article has been accepted for publication in IEEE Access.

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Section: Discussionmentioning

confidence: 99%

Section: Safety Consideration For Power Electronic Systemmentioning

confidence: 99%

Power Distribution and Propulsion System for an All-Electric Short-Range Commuter Aircraft—A Case Study

et al. 2022

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“…The flexibility offered by the increased number of switch positions and multiple redundant commutation paths results in improved post-fault performance. 'Limp home' operational mode can be implemented, and the inverter can continue to operate at reduced power [42,43]. This is essential for safety-critical application areas such as aviation.…”

Section: Three-phase Three-level (A)npc Modulationmentioning

confidence: 99%

Review, Comprehensive Analysis and Derivation of Analytical Power Loss Calculation Equations for Two- to Three-Level Midpoint Clamped Inverter Topologies with Hybrid Switch Configurations

Radomsky,

Mallwitz

2023

Energies

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Increased performance requirements in new power electronics areas of application, such as electric aircraft, make innovations on different design levels necessary. In order to quickly compare different topologies, analytical loss equations provide a fast and straightforward way to narrow down the possible solution space. The approach widely used in the literature results in long and complex terms, which can only be compared between different literature sources with great effort. Moreover, the literature lacks a detailed summarizing description of these analytical equations and their derivation, starting from the standard two-level VSI up to three-level midpoint clamped inverter topologies, such as the ANPC topology in its different modulation schemes. The application of such higher-level inverter topologies allows hybrid device configurations to become performant solutions. This work aims to give a closed-form description of the analytical loss modeling and the theoretical background and provide an implementation approach for a wide span of inverter topologies and for different modulation methods.

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“…Furthermore, less stress will be applied to the isolation system since smaller voltage steps can be achieved with such kind of topology. In case of single device failure, several fault-tolerant operation strategies can be applied to improve the postfault performance [14], [15].…”

Section: ) Electric Motor and Propellermentioning

confidence: 99%

Inverter design for future electrified aircraft propulsion systems under consideration of wear-out failure and random failure

Cao,

Fauth,

Keuter

et al. 2023

2023 25th European Conference on Power Electronics and Applications (EPE'23 ECCE Europe)

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To reduce the wear-out effect and minimize the Single Event Burnout effect of the power semiconductor, several hardware design rules for inverters in electric aircraft propulsion systems are posed and implemented in this work. These strategies include scalable chip area and derated DC-link voltage. It is observed in a short-range reference aircraft case study that these rules could result in a conflict of objectives: reducing the risk of wear-out failure while simultaneously minimizing the risk of random failure. Therefore, it is recommended to consider random failures, wear-out failures, and their mutual impacts in a comprehensive analysis of system reliability. A reliabilityoriented design rule is proposed in this work.

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Comparison and Analysis of Multi-State Reliability of Fault-Tolerant Inverter Topologies for the Electric Aircraft Propulsion System

Cited by 7 publications

References 15 publications

Power Distribution and Propulsion System for an All-Electric Short-Range Commuter Aircraft—A Case Study

Power Distribution and Propulsion System for an All-Electric Short-Range Commuter Aircraft—A Case Study

Review, Comprehensive Analysis and Derivation of Analytical Power Loss Calculation Equations for Two- to Three-Level Midpoint Clamped Inverter Topologies with Hybrid Switch Configurations

Inverter design for future electrified aircraft propulsion systems under consideration of wear-out failure and random failure

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