Influences of voltage variations on electric power architectures for hybrid electric aircraft

Vratny, Patrick C.; Kuhn, H.; Hornung, Mirko

doi:10.1007/s13272-016-0218-z

Cited by 31 publications

(35 citation statements)

References 6 publications

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“…A power management and distribution (PMAD) system in form of inverters, converters and cables is needed to ensure safe operation of the motor controlling the voltage and current levels [28]. State-of-the-art electric motors are not often designed for applications with weight limitations and have gravimetric power densities between 2-10 kW/kg [5].…”

Section: Electric Propulsion Componentsmentioning

confidence: 99%

“…As a design requirement for the PMAD components the rated voltage of the electric propulsion system is needed. Vratny et al [28] and Jones et al [36] prove that a system voltage of 3 kV (DC) leads to the highest efficiency for all electric demands, which is chosen for the simulation. Voltage variations are handled by the converters and inverters.…”

Section: Electric Propulsion Componentsmentioning

confidence: 99%

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Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

et al. 2018

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Ambitious targets to reduce emissions caused by aviation in the light of an expected ongoing rise of the air transport demand in the future drive the research of propulsion systems with lower CO 2 emissions. Regional hybrid electric aircraft (HEA) powered by conventional gas turbines and battery powered electric motors are investigated to test hybrid propulsion operation strategies. Especially the role of the battery within environmentally friendly concepts with significantly reduced carbon footprint is analyzed. Thus, a new simulation approach for HEA is introduced. The main findings underline the importance of choosing the right power-to-energy-ratio of a battery according to the flight mission. The gravimetric energy and power density of the electric storages determine the technologically feasibility of hybrid concepts. Cost competitive HEA configurations are found, but do not promise the targeted CO 2 emission savings, when the well-to-wheel system is regarded with its actual costs. Sensitivity studies are used to determine external levers that favor the profitability of HEA.

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Section: Electric Propulsion Componentsmentioning

confidence: 99%

Section: Electric Propulsion Componentsmentioning

confidence: 99%

Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

et al. 2018

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“…The SUGAR team design has made a selection for a 10 kV system architecture for the system studies [29,179]. Vratny et al study presented an impact analysis for selection between a constant system voltage (CSV) and a variable system voltage (VSV) architecture for a battery powered 6000 kW electrical drive system [180]. In the CSV design, the decreasing output voltage from the battery is compensated with a converter, whereas in VSV design, the voltage output from battery was directly fed to the motor inverter.…”

Section: High Voltage Architecture and Protectionmentioning

confidence: 99%

“…The heat sinks appropriate for the TMS are fuel, fan bypass/ ram air, and coolants, and heat exchanger designs vary as a fuel oil cooler and air oil cooler. The architectural lay out can be made as centralized/decentralized [180], parallel/serial [31] systems, etc., optimized based on the placement and sizing of the head load components. Coolants are typically single phase or two-phase; some of the suitable coolants are listed in the literature [180].…”

Section: Thermal Management System Challenges and Developmentsmentioning

confidence: 99%

“…An accurate prediction of electrical system weight and volume can be made if the voltage standards are defined. At the same time, an optimum selection of voltage level can be made with a holistic approach, accounting for all the performances of individual components [180]. Additionally, the optimum design should be adopted through an advanced algorithm based approach, considering the thermal stability and power quality in balance with system mass and efficiency [175].…”

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confidence: 99%

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A Review of Concepts, Benefits, and Challenges for Future Electrical Propulsion-Based Aircraft

2020

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Electrification of the propulsion system has opened the door to a new paradigm of propulsion system configurations and novel aircraft designs, which was never envisioned before. Despite lofty promises, the concept must overcome the design and sizing challenges to make it realizable. A suitable modeling framework is desired in order to explore the design space at the conceptual level. A greater investment in enabling technologies, and infrastructural developments, is expected to facilitate its successful application in the market. In this review paper, several scholarly articles were surveyed to get an insight into the current landscape of research endeavors and the formulated derivations related to electric aircraft developments. The barriers and the needed future technological development paths are discussed. The paper also includes detailed assessments of the implications and other needs pertaining to future technology, regulation, certification, and infrastructure developments, in order to make the next generation electric aircraft operation commercially worthy.

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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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Influences of voltage variations on electric power architectures for hybrid electric aircraft

Cited by 31 publications

References 6 publications

Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

Conceptual Design of Operation Strategies for Hybrid Electric Aircraft

A Review of Concepts, Benefits, and Challenges for Future Electrical Propulsion-Based Aircraft

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

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