Architecture design and performance analysis of a hybrid hydrogen fuel cell system for unmanned aerial vehicle

Ozbek, Emre; Yalin, Gorkem; Karaoğlan, Mustafa Umut; Ekici, Selçuk; Çolpan, C. Özgür; Karakoç, T. Hikmet

doi:10.1016/j.ijhydene.2020.12.216

Cited by 54 publications

(10 citation statements)

References 14 publications

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“…Similarly, switching control logic is designed in [59] for a fuel cell/ PV hybrid system. In [60], a fuel cell/LiPo battery hybrid system is built to evaluate the performance of three architecture models. power, whereas the battery/supercapacitor will deal with the high-frequency power demand [61].…”

Section: A Rule-based Emsmentioning

confidence: 99%

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

Huangfu

et al. 2022

IEEE Trans. Transp. Electrific.

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Unmanned aerial vehicles (UAVs) can be regarded as one of the most emerging technologies. Compared with piloted aerial vehicles, UAVs qualify for higher safety and lower cost, and they are more suitable for dangerous missions. Recently, fuel cell UAVs have obtained more and more attention due to their relatively higher energy density. However, their propulsion system still needs to be further improved to meet different requirements of performing difficult tasks. This article aims to give a comprehensive review of the key technologies of fuel cell UAVs. Firstly, various architectures of the propulsion system and corresponding advantages and disadvantages are introduced. Then, three kinds of management strategies for fuel cell UAVs are reviewed. Next, some special applications and considered design procedures are summarized. Compared with other review papers, this paper tries to cover more aspects of fuel cell UAVs. Since these aspects have a tight relationship with each other, giving a comprehensive review can be more beneficial to us to understand the state-of-the-art development of propulsion systems for fuel cell UAVs. The conclusions show that advanced propulsion architectures, efficient online energy management strategies, and professional design procedures are still in urgent demand in the commercial process of fuel cell UAVs.

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Section: A Rule-based Emsmentioning

confidence: 99%

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

Huangfu

et al. 2022

IEEE Trans. Transp. Electrific.

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“…The first one is the improvement of efficiency of thermal systems whereas the second one is investigation of new energy sources instead of using for fossil fuels. Recently, hybrid systems, fuel-cell technologies and biofuels have sparked interest to the engineers [3][4][5][6]. In this context, optimization of energetic and exergetic parameters for propulsion system is being deployed as the main technique in the effort to evaluating the gas turbine engine performance.…”

Section: Introductionmentioning

confidence: 99%

Optimization of energy and exergy parameters for a conceptual after burning turbojet engine

Aygün

2023

Journal of Thermal Engineering

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In this study, parametric cycle analysis of a conceptual turbojet engine with an afterburner (TJEAB) was conducted at sea level conditions-zero Mach. Based on this analysis, exergetic sustainability parameters of TJEAB were scrutinized for military mode (MM) and afterburner mode (ABM). Constitutively, several design parameters of TJEAB were chosen so as to optimize performance and exergetic parameters which consist of specific fuel consumption (SFC), overall efficiency, exergy efficiency, environmental effect factor (EEF) and exergetic sustainability index (ESI). In this context, compressor pressure ratio (CPR), turbine inlet temperature (TIT) were preferred due to high effect of these variables on engine performance. CPR ranges from 4 to 11 whereas TIT varies from 1150 K to 1550 K. According to optimization of performance parameters, minimum SFC was achieved as 28.59 g/kN.s at MM and 43.95 g/kN.s at ABM. On the other hand, maximum overall efficiency is determined as to be 13.07 % at MM and to be 8.5 % at ABM. As for exergetic parameters, exergy efficiency was calculated as maximum with 30.85 % at MM and 23.2 %at ABM. Finally, maximum exergetic sustainability index of TJEAB was computed as 0.446 at MM and 0.269 at ABM. It is thought that energetic and exergetic parameters analyzed in this analysis could guide in designing turbojet engines in terms of lower fuel consumption thereby environmental-benign.

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“…The UAV is used for telecommunications and atmospheric monitoring both manufactured by AeroVironment (Writer, 2020). In addition, a hybrid UAV test bed consisting of hydrogen fuel cells and lipo batteries was realized by Eskisehir Technical University (Ozbek et al, 2020(Ozbek et al, , 2021. Another example is the AAI Aerosonde, which is powered by an Enya R120 engine and is designed to collect weather data such as temperature, pressure and humidity (Writer, 2020).…”

Section: Introductionmentioning

confidence: 99%

Development of a novel supervisory controller on a parallel-hybrid powertrain for small unmanned aerial systems

Fouellefack

Smith

Krüger

2022

AEAT

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Purpose A hybrid-electric unmanned aerial vehicle (HE-UAV) model has been developed to address the problem of low endurance of a small electric UAV. Electric-powered UAVs are not capable of achieving a high range and endurance due to the low energy density of its batteries. Alternatively, conventional UAVs (cUAVs) using fuel with an internal combustion engine (ICE) produces more noise and thermal signatures which is undesirable, especially if the air vehicle is required to patrol at low altitudes and remain undetected by ground patrols. This paper aims to investigate the impact of implementing hybrid propulsion technology to improve on the endurance of the UAV (based on a 13.6 kg UAV). Design/methodology/approach A HE-UAV model is developed to analyze the fuel consumption of the UAV for given mission profiles which were then compared to a cUAV. Although, this UAV size was used as reference case study, it can potentially be used to analyze the fuel consumption of any fixed wing UAV of similar take-off weight. The model was developed in a Matlab-Simulink environment using Simulink built-in functionalities, including all the subsystem of the hybrid powertrain. That is, the ICE, electric motor, battery, DC-DC converter, fuel system and propeller system as well as the aerodynamic system of the UAV. In addition, a ruled-based supervisory controlled strategy was implemented to characterize the split between the two propulsive components (ICE and electric motor) during the UAV mission. Finally, an electrification scheme was implemented to account for the hybridization of the UAV during certain stages of flight. The electrification scheme was then varied by changing the time duration of the UAV during certain stages of flight. Findings Based on simulation, it was observed a HE-UAV could achieve a fuel saving of 33% compared to the cUAV. A validation study showed a predicted improved fuel consumption of 9.5% for the Aerosonde UAV. Originality/value The novelty of this work comes with the implementation of a rule-based supervisory controller to characterize the split between the two propulsive components during the UAV mission. Also, the model was created by considering steady flight during cruise, but not during the climb and descend segment of the mission.

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Architecture design and performance analysis of a hybrid hydrogen fuel cell system for unmanned aerial vehicle

Cited by 54 publications

References 14 publications

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

Optimization of energy and exergy parameters for a conceptual after burning turbojet engine

Development of a novel supervisory controller on a parallel-hybrid powertrain for small unmanned aerial systems

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