Conceptual Design of an Electric Propulsion System Based on Fuel Cells for an Ultralight Manned Aircraft

Geliev, A. V.; Varyukhin, Anton; Zakharchenko, V. S.; Kiselev, I.O.; Zhuravlev, Denis

doi:10.1109/icoecs46375.2019.8949950

Cited by 9 publications

(9 citation statements)

References 4 publications

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“…Batteries or other electric storage systems are usually coupled with the fuel cell in a hybrid electric architecture to overcome its limitations( [3], [4]. A compressed or liquified hydrogen vessel has higher gravimetric energy density but lower volumetric energy density than lithium batteries, while the fuel cell has a low power density compared with the battery [5].…”

Section: Introductionmentioning

confidence: 99%

“…The role of the battery in a fuel cell system is also to overcome the slower dynamic response of the fuel cell. More than ten seconds may elapse from giving a command to reaching the desired power [3]. Hybridization, on the other hand, requires efficient energy management strategies and a careful consideration of operating conditions and technological limits.…”

Section: Introductionmentioning

confidence: 99%

“…Sizing a fuel cell system for ultralight aviation is not a trivial task because there are several key factors to consider [6]. The size of the fuel cell is often arbitrarily selected [3] or put equal to the cruise power in a single specific mission [7]. Some studies propose an optimization of the fuel cell system using as a metric the hydrogen fuel consumption and the total mass [8][9].…”

Section: Introductionmentioning

confidence: 99%

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Preliminary design of a retrofitted ultralight aircraft with a hybrid electric fuel cell power system

Donateo,

Ficarella,

Lecce

2024

J. Phys.: Conf. Ser.

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Emission-free aerial propulsion can be achieved with a proton-exchange membrane fuel cell (PEM-FC). In the present investigation, this potential is addressed by designing a hybrid electric power system with fuel cells for an ultralight aerial vehicle to be retrofitted from a conventional fossil-fuelled piston engine configuration. The proposed power system includes a fuel cell, a lithium battery, and a compressed hydrogen vessel. A procedure is proposed to find the size of these components that minimizes the total mass and satisfies the target of a size below 200L and uses performance data of commercially available components. A comparison of different energy management approaches, with and without on-board charge of the battery, is performed. The results underline that the optimal solution is to select the size of the fuel cell to meet the cruise electric request and point out that the maximum discharge current of the battery must be regarded as a key issue in sizing this component, because of the very high take-off power.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Preliminary design of a retrofitted ultralight aircraft with a hybrid electric fuel cell power system

Donateo,

Ficarella,

Lecce

2024

J. Phys.: Conf. Ser.

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“…This calls for implementation of a novel electric power distribution topology. While designing the electric power system (EPS) for More Electric Aircrafts, the following points need to be considered: choice of electric power system architecture (Barzkar and Ghassemi, 2020; Alexander et al , 2018; Jiao et al , 2020; Wang et al , 2019; Chen et al, 2018; Martínez et al , 2022; Cano et al , 2021; Madonna et al , 2018; Zhu et al , 2021; Brombach et al , 2012; Lawhorn et al , 2018; Ghassemi and Saghafi, 2022); choice of power electronic converters for the chosen EPS architecture (Patnaik et al , 2022; Gu et al , 2020; Harikumaran et al , 2021; Nøland et al , 2019; Ni et al , 2019; Clements and Jones, 2018; Buticchi et al , 2018; Vishal et al , 2022); choice of auxiliary energy source (Ansell, 2022; Wu and Li, 2014; Rajashekara and Jia, 2016; Chen and Song, 2019; Bradley, 2022; Geliev et al , 2019; Kreutzer et al , 2016; Dai et al , 2017; Yu et al , 2022; Kreutzer et al , 2018; Fei et al , 2021); and choice of control scheme for the efficient use of primary and auxiliary energy sources (Wen and Zheng, 2018; Kumar et al , 2017; Pandey et al , 2020; Wang et al , 2016; Zhang et al , 2020; Jangir et al , 2017; Xu et al , 2016; Kumar et al , 2017; Karthikeyan and Gupta, 2015; Wang et al , 2015). …”

Section: Introductionmentioning

confidence: 99%

“…choice of auxiliary energy source (Ansell, 2022; Wu and Li, 2014; Rajashekara and Jia, 2016; Chen and Song, 2019; Bradley, 2022; Geliev et al , 2019; Kreutzer et al , 2016; Dai et al , 2017; Yu et al , 2022; Kreutzer et al , 2018; Fei et al , 2021); and…”

Section: Introductionmentioning

confidence: 99%

Implementation and performance analysis of a novel sliding mode controller for bidirectional DC to DC converter in aircraft application

Karvekar¹,

Joshi²

2023

WJE

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Purpose The purpose of this paper is to implement a closed loop regulated bidirectional DC to DC converter for an application in the electric power system of more electric aircraft. To provide a consistent power supply to all of the electronic loads in an aircraft at the desired voltage level, good efficiency and desired transient and steady-state response, a smart and affordable DC to DC converter architecture in closed loop mode is being designed and implemented. Design/methodology/approach The aircraft electric power system (EPS) uses a bidirectional half-bridge DC to DC converter to facilitate the electric power flow from the primary power source – an AC generator installed on the aircraft engine’s shaft – to the load as well as from the secondary power source – a lithium ion battery – to the load. Rechargeable lithium ion batteries are used because they allow the primary power source to continue recharging them whenever the aircraft engine is running smoothly and because, in the event that the aircraft engine becomes overloaded during takeoff or turbulence, the charged secondary power source can step in and supply the load. Findings A novel nonsingular terminal sliding mode voltage controller based on exponential reaching law is used to keep the load voltage constant under any of the aforementioned circumstances, and its performance is contrasted with a tuned PI controller on the basis of their respective transient and steady-state responses. The former gives a faster and better transient and steady-state response as compared to the latter. Originality/value This research gives a novel control scheme for incorporating an auxiliary power source, i.e. rechargeable battery, in more electric aircraft EPS. The battery is so implemented that it can get regeneratively charged when primary power supply is capable of handling an additional load, i.e. the battery. The charging and discharging of the battery is carried out in closed loop mode to ensure constant battery terminal voltage, constant battery current and constant load voltage as per the requirement. A novel sliding mode controller is used to improve transient and steady-state response of the system.

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Developing an inverter controlling electric motor for small air transport

Zagumennov

Varyukhin

Казаков

et al. 2021

J. Phys.: Conf. Ser.

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This paper provides a concept for developing inverters for high power aircraft brushless motors. It should be noted that such devices have an increased number of safety solutions, stable rotor synchronization parameters, and an increased number of isolated hardware nodes. The main result of this study is an engine motor controller with a power of up to 60 kW with control through optical fiber, liquid cooling, completely isolated power and control circuits, overcurrent, inverter and motor temperature protection, synchronization by Hall sensors. This paper also contains the calculation of the cost of introducing such solutions into a typical inverter.

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Conceptual Design of an Electric Propulsion System Based on Fuel Cells for an Ultralight Manned Aircraft

Cited by 9 publications

References 4 publications

Preliminary design of a retrofitted ultralight aircraft with a hybrid electric fuel cell power system

Preliminary design of a retrofitted ultralight aircraft with a hybrid electric fuel cell power system

Implementation and performance analysis of a novel sliding mode controller for bidirectional DC to DC converter in aircraft application

Developing an inverter controlling electric motor for small air transport

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