Comparison of lithium ion Batteries, hydrogen fueled combustion Engines, and a hydrogen fuel cell in powering a small Unmanned Aerial Vehicle

Depcik, Christopher; Cassady, Truman; Collicott, Bradley; Burugupally, Sindhu Preetham; Li, Xianglin; Alam, Shah Saud; Arandia, Jose Rocha; Hobeck, Jared D.

doi:10.1016/j.enconman.2020.112514

Cited by 127 publications

(39 citation statements)

References 67 publications

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“…In the horizontal (x) direction, thrust force (F T ) should be equal to the drag force (F D ) according to the conservation of momentum, therefore the equation could be described as [17]:…”

Section: Uav Power Requirementmentioning

confidence: 99%

“…Compressed hydrogen storage is the most common method for UAV applications however this method requires extremely high pressures. Lately, although the weight of compressed tanks has been significantly reduced with the new composite technology, the different methods such as liquid hydrogen and sodium borohydride continue to be explored [7,8,13,16,17]. In one of these studies, with the use of liquid hydrogen, exceeding 48 hours endurance was recorded [8].…”

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confidence: 99%

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Conceptual Design of Fuel Cell Based Hybrid Unmanned Air Vehicle

Keiyinci

Aydın

2021

European Mechanical Science

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An unmanned air vehicle (UAV) is a non-human air vehicle controlled autonomously by plugged microprocessors or telemetrically by an operator on the ground [1]. UAVs have received great interest in the last decades with many different usage missions for military and civilian areas [2]. As a result of this interest, many countries and institutions are making significant investments in this field. UAV market value is expected to reach $52.30 billion by 2025 [3]. Recently interest in electric powered small UAVs has increased gradually because of its high efficiency, high reliability, low cost and reduced noise [4]. Considering issues such as insurance, license, maintenance, pilot license and flight permits, it is anticipated that small unmanned aerial vehicles will be used more in the future. Moreover, from a military point of view, it is known that the need for maneuverable UAVs of small sizes suitable for use in rugged terrain and residential areas is increasing. The primary problem encountered in small UAVs, especially in the field of imaging and intelligence, is the limit of the endurance and range. As the size of the air vehicle minimizes, the use of reciprocating and gas turbine engines becomes more difficult. On the other hand, battery systems using in electric UAVs cannot provide enough energy particularly in case of long endurance missions. Increa

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“…In the horizontal (x) direction, thrust force (F T ) should be equal to the drag force (F D ) according to the conservation of momentum, therefore the equation could be described as [17]:…”

Section: Uav Power Requirementmentioning

confidence: 99%

mentioning

confidence: 99%

Conceptual Design of Fuel Cell Based Hybrid Unmanned Air Vehicle

Keiyinci

Aydın

2021

European Mechanical Science

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“…A detailed analysis of synergetic effects for various classes of UAVs is given in [8] by applying the multi-objective optimization, where results have shown that hybrid-electric configuration has the potential to give a strong contribution to aircraft performance. Moreover, by investigating the behavior of different power sources within the UAV hybrid-electric propulsion system through simulations in order to predict the hybrid electric power system behavior using bench tests, the feasibility and efficiency of the onboard UAV power system can be assessed before the final flight test phase [9]. Also, a comparison of five different UAV power-train options has been investigated in [9] using simulations.…”

Section: Introductionmentioning

confidence: 99%

Modeling, Control System Design and Preliminary Experimental Verification of a Hybrid Power Unit Suitable for Multirotor UAVs

et al. 2021

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A key drawback of multirotor unmanned aerial vehicles (UAVs) with energy sources based solely on electrochemical batteries is related to the available on-board energy. Flight autonomy is typically limited to 15–30 min, with a flight duration upper limit of 90 min currently being achieved by high-performance battery-powered multirotor UAVs. Therefore, propulsion systems that utilize two or more different energy sources (hybrid power systems) may be considered as an alternative in order to increase the flight duration while retaining key performance benefits of battery energy storage use. The research presented in this work considers a multirotor UAV power unit, based on the internal combustion engine (ICE) powering an electricity generator (EG) connected to the common direct current (DC) bus in parallel with the lithium-polymer (LiPo) battery, and the respective modeling and identification of individual power unit subsystem, along with the dedicated control system design. Experimental verification of the proposed hybrid power unit control system has been carried out on the custom-build power unit prototype. The results show that the proposed control system combines the two power sources in a straightforward and effective way, with subsequent analysis showing that a two-fold energy density increase can be achieved with a hybrid energy source, consequently making it possible to achieve higher flight autonomy of the prospective multirotor (hover load around 1000–1400 W) equipped with such a hybrid system.

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“…The study of acoustic supercharging on alternative fuels is rare despite the global tendency in transport domain to use these fuels mainly the LPG and H 2 . 20–23 The novelty of this research is, therefore, the combination of variable intake manifold design based on quart wave resonance technique and verification of acoustic supercharging on air-alternative fuels blends. Moreover, the study of the effect of hydrogen enrichment with LPG on the engine acoustic filling presents a second part of novelty.…”

Section: Introductionmentioning

confidence: 99%

Variable intake manifold geometry influence on volumetric efficiency enhancement at gaseous engine starting speeds

Jemni

Hadjkacem

Ammar

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part E:

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This paper studied the effect of variable intake length manifold on filling and volumetric efficiency at starting engine speeds using numerical and experimental process. The investigation is based on acoustic supercharging phenomenon. For this purpose, 1-D engine gas-flow model was developed and optimum intake lengths for several low engine speeds were determined using acoustic theory based-resolution. Using the method of characteristics, pressure waves were predicted at the end of intake line length (intake valve level) in order to test the dynamic inertial supercharging phenomena. The quarter-wave resonator technique was taken into consideration to explore the inlet pressure pulsations. Simulations of pressure wave propagation were achieved during intake stroke and intake valve closed phase. Simulation predictions confirmed the analytically calculated optimum intake length. Numerical investigations were carried out on five in-cylinder flow moving through intake system; air, air-gasoline, air-LPG, air-H2 and air-LPG-H2 blend. The percentages of supplied hydrogen with LPG were 0%, 5%, 10%, 15% and 20% in volume. To experimentally validate the analytical founded lengths, an instrumented cold-flow four cylinder Ford SI engine test bench was prepared. Flow through variable intake length manifold was analyzed. Geometry variation was performed on the plenum length. Three engine low speeds are tested; 500 rpm, 750 rpm and 1000 rpm. The experiment results showed an in-cylinder velocity increase by about 60%, 58% and 48% using the optimal intake length at 500 rpm, 750 rpm and 1000 rpm respectively. Furthermore, the collected data proves that varying intake pipe length continuously with the engine speed leads to an average of 39.7% improvement in volumetric efficiency from the original engine configuration at 1000 rpm.

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Comparison of lithium ion Batteries, hydrogen fueled combustion Engines, and a hydrogen fuel cell in powering a small Unmanned Aerial Vehicle

Cited by 127 publications

References 67 publications

Conceptual Design of Fuel Cell Based Hybrid Unmanned Air Vehicle

Conceptual Design of Fuel Cell Based Hybrid Unmanned Air Vehicle

Modeling, Control System Design and Preliminary Experimental Verification of a Hybrid Power Unit Suitable for Multirotor UAVs

Variable intake manifold geometry influence on volumetric efficiency enhancement at gaseous engine starting speeds

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