Energy Conversion System and Control of Fuel-Cell and Battery-Based Hybrid Drive for Light Aircraft

Miazga, Tomasz; Iwański, Grzegorz; Nikoniuk, Marcin

doi:10.3390/en14041073

Cited by 8 publications

(4 citation statements)

References 16 publications

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“…The family of lithium batteries is quite vast and, consequently, battery specifications like energy density, 𝐶 𝑟𝑎𝑡𝑒,𝑑𝑖𝑠 , and 𝐶 𝑟𝑎𝑡𝑒,𝑐ℎ have a large range of variation [9]. Actually, there is a trade-off between energy density and maximum battery power/current, so batteries designed to achieve very high values of energy density are characterized by limited discharging currents and consequently, low power density ([14], [7]). In this investigation, lithium polymer batteries are adopted.…”

Section: Technological Scenariomentioning

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: Technological Scenariomentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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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“…Other studies have dealt with the same approach to preliminarily design various components of all-electric propulsion systems which were separately sized with simplified models [16,17]. In [18] a propulsive architecture similar to that proposed in this study is analyzed focusing on the energy conversion and the control system: the types of DC/DC and DC/AC converters, including the technologies on which they are based, are evaluated to find the optimal solution for coupling the electric sources and the motor. This study has been conducted to cover the lack in the literature of a numerical model that includes dynamics of the electrical behavior of a system from the electrochemical sources to the aircraft propeller.…”

Section: State-of-the-artmentioning

confidence: 99%

From a Battery-Based to a PEM Fuel Cell-Based Propulsion Architecture on a Lightweight Full Electric Aircraft: A Comparative Numerical Study

2022

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The aviation sector is firmly committed to reducing harmful emissions and electric propulsion promises to tackle both pollution and noise at the same time. More Electric Aircrafts are progressively giving way to full electric aircraft that are expected to represent the next revolution in aviation. As is known, electric propulsion can be based on different electrochemical sources; nowadays, the widely used systems are developed on lithium battery packs, especially in automotive, where requirements in terms of gravimetric and volumetric energy densities are not so stringent compared to the aeronautical sector. Systems based on hydrogen fuel cells exhibit better performance in terms of range and endurance. In this article, a numerical study is presented on a lightweight electric aircraft, whose battery-based architecture is converted to a fuel cell-based architecture with the contribution of a battery pack that essentially intervenes in the take-off phase and, in addition, of a pack of ultracapacitors to prevent high discharge rate of the battery. The final intent is to explore the range extension without an increase in maximum take-off weight. The lumped parameter numerical models of the two propulsion systems have been developed in Simcenter Amesim where a set of simulations has been launched. It is shown that even under the constraint on the maximum take-off weight a significant extension of the range is obtained when adopting an electric propulsion system based on hydrogen fuel cells.

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“…For example, as part of its Green Deal, the European Commission has formulated the goal of zero-emission aircraft being ready for the market by 2035 (European Commission, 2020). Across the globe, a broad range of research initiatives is being implemented which focus on electrified propulsion systems (Pohl et al, 2022;Hofmann et al, 2019;Hoelzen et al, 2018), fuel cell technology (Miazga et al, 2021;Scholz et al, 2022) and sustainable aviation fuels (Abrantes et al, 2021;Holladay et al, 2020). One such upcoming trend and transfer technology into full electrical propulsion systems will be hybridization until sufficiently high energy densities are achieved for battery cells, as shown by Pornet et al (2015).…”

Section: Introductionmentioning

confidence: 99%

Functional Hazard Assessment of the Propulsion Control System Designed for a Small Hybrid Electric Aircraft

Motte¹,

Niehuis²,

Fischer³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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This paper presents the Functional Hazard Assessment (FHA) of a Propulsion Control System (PCS) designed for a hybrid electric aircraft considering the Failure Conditions (FCs) that are novel due to the electrification of the propulsion system. It will be worked out whether these FCs are covered by current certification regulations. After defining the functionality, the FCs for a hybrid electric propulsion system are established, based on current standards and also the Working Group 113 (WG-113) recommendations. The FHA and Preliminary System Safety Assessment (PSSA) approaches are used to evaluate and improve the architecture of the control system. The system functions on propulsion level are defined and allocated to different subsystems. Their FCs and effects are then established. Based on the applicable standards and recommendations of WG-113, these effects are classified, and the Safety Requirements (SRs) are then defined. The FHA results include 23 FCs related to the hybrid system, some of which are not addressed by the current regulatory framework. In summary, this paper outlines how electrified powertrain systems will affect new propulsion architectures from a safety perspective and how the current regulatory framework and the work of the WG-113 could be improved by addressing new FCs resulting from the FHA. By suggesting SRs derived from the FHA, this paper also discusses what system/safety activities need to be undertaken in order to design a propulsion architecture that is compliant with the applicable certification documents.

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Energy Conversion System and Control of Fuel-Cell and Battery-Based Hybrid Drive for Light Aircraft

Cited by 8 publications

References 16 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

From a Battery-Based to a PEM Fuel Cell-Based Propulsion Architecture on a Lightweight Full Electric Aircraft: A Comparative Numerical Study

Functional Hazard Assessment of the Propulsion Control System Designed for a Small Hybrid Electric Aircraft

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