Modelling and Simulation of Fuel Cell Dynamics for Electrical Energy Usage of Hercules Airplanes

Radmanesh, Hamid; Yazdi, Seyed Saeid Heidari; Gharehpetian, Gevork B.; Fathi, S. H.

doi:10.1155/2014/593121

Cited by 3 publications

(3 citation statements)

References 27 publications

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“…The lumped parameter approach has been successfully used for the analysis of hybrid-electric propulsive architectures [13][14][15]. 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.…”

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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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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“…A PID controller was used to regulate the output voltage at a certain set point via controlling the flow rate of hydrogen and oxygen for a hybrid power-plant system of a 240 W PEM fuel cell stack used for a C-130 Hercules aircraft, as reported by [24].…”

Section: Pid Controller For Air and Hydrogen Supplymentioning

confidence: 99%

Environmental Impact of High Altitudes on the Operation of PEM Fuel Cell Based UAS

Saleh¹,

Ali²,

Zhang³

2018

EPE

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Fuel cell is a device that converts the chemical energy in the reactants into the electrical energy after steps of sequential electrochemical processes with no significant impact on the environment. For high altitude long endurance (HALE) of unmanned aircraft system (UAS) where fuel cell operates as a prime source of power, the operation and performance of a PEM fuel cell at different level of altitudes is vitally important. In this paper, the impact of direct using extracted air from high altitudes atmosphere in order to feed the stack is investigated, and the governing equations of the supplied air and oxygen to the PEM fuel cell stack are developed. The impact of high altitudes upon the operation and the consumption of air are determined in order to maintain certain level of delivered power to the load. Also the implications associated with operating the PEM fuel cell stack at high altitudes and different technical solutions are proposed. Various modes of Integral, Proportional-Integral, and Proportional-Integral-Derivative controller are introduced and examined for different time setting responses in order to determine the most adequate trade-off choice between fast response and reactants consumption which provides the necessary optimization of the air consumption for the developed model of PEM fuel cell used for UAS operation.

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“…Radmanesh et al [7] reported that storing hydrogen in the form of highly pressurised gas is the cheapest method, due to developments in composite materials that offer storing pressure up to 800 bar. However, pressurised hydrogen gas is usually stored in steel tanks with a pressure range between 200 and 300 bar.…”

Section: Introductionmentioning

confidence: 99%

Pressure Vessel Mass Estimation for High Altitude PEM Unmanned Aircraft System

Albayati,

Ali,

Al-Bayati

2024

Preprint

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The power to weight ratio of the power plant is an important consideration, especially in design of Unmanned Aircraft System (UAS). In this paper, a UAS with an MTOW of 35.3 kg, equipped with a fuel cell as a prime power supply to provide electrical power to the propulsion system is being considered. A pressure vessel design is proposed that can estimate and determine the total size and weight of the combined power-plant of a fuel cell stack with hydrogen and air/oxygen vessels and the propulsion system of the UAS for high altitude operation. Two scenarios are adopted in determining the size and weight of pressure vessels required to supply oxygen to the fuel cell stack. Different types of stainless-steel materials are used in the design of the pressure vessel in order to find an appropriate material that provides low size and weight advantages. Also, hydrogen pressure vessel design and mass estimation are also considered. The estimated sizes and weights of hydrogen and oxygen vessels of the power-plant and propulsion system in this research offers a maximum of four hours of flying time for the UAS mission; this is based on a Horizon (H-1000) PEM stack.

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Modelling and Simulation of Fuel Cell Dynamics for Electrical Energy Usage of Hercules Airplanes

Cited by 3 publications

References 27 publications

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

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

Environmental Impact of High Altitudes on the Operation of PEM Fuel Cell Based UAS

Pressure Vessel Mass Estimation for High Altitude PEM Unmanned Aircraft System

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