Maximum Take-Off Mass Estimation of a 19-Seat Fuel Cell Aircraft Consuming Liquid Hydrogen

Marksel, Maršenka; Brdnik, Anita Prapotnik

doi:10.3390/su14148392

Cited by 8 publications

(12 citation statements)

References 15 publications

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“…The specific fuel consumption of a current aircraft powered by a fuel cell system is estimated as b F, FC ¼ 0:025 kg MJ , using the method described by Marksel and Prapotnik Brdnik. 31 By that, a range of R ¼ 519 km is calculated, which demonstrates that the storable hydrogen mass is generally suitable for realizing a general aviation aircraft with a reasonable operational capability.…”

Section: Optimization Resultsmentioning

confidence: 78%

“…In order to demonstrate the practical use of the storable hydrogen mass, the range of the aircraft is estimated using the linearized Breguet range equation for propeller-driven aircraftwith L/D=16 being a typical lift-to-drag ratio of a contemporary general aviation aircraft, ηProp=0.8 being a typical propeller efficiency according to Marksel and Prapotnik Brdnik, 31 mH2 being the hydrogen mass normalized by the inner wingspan binner=9.25 m, as given in Table 4 and mTO being the take-off mass according to Table 1. The specific fuel consumption of a current aircraft powered by a fuel cell system is estimated as bF,FC=0.025 kgMJ, using the method described by Marksel and Prapotnik Brdnik.…”

Section: Wing Optimization Examplementioning

confidence: 99%

See 1 more Smart Citation

Design studies for a light aircraft wing with highly integrated load-bearing hydrogen tanks using multi-objective optimization methods

Friedmann

Rienecker

Dexl

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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To enable emission-free flight, the use of hydrogen as an energy carrier in aircraft is one possible solution. However, hydrogen storage is a challenging task. The current paper presents a design study for a light aircraft wing with highly integrated load-bearing hydrogen tanks using an automated optimization method by means of Evolutionary Algorithms. With this method, both preliminary investigations and a more detailed design of structural wing concepts with highly integrated hydrogen vessels were carried out.

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Section: Optimization Resultsmentioning

confidence: 78%

Section: Wing Optimization Examplementioning

confidence: 99%

Design studies for a light aircraft wing with highly integrated load-bearing hydrogen tanks using multi-objective optimization methods

Friedmann

Rienecker

Dexl

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Flight characteristics primarily depend on four parameters: payload, range, wing loading, and power loading [23], where the results of the constraint analysis indicate that amphibious category aircraft has higher values (35%-80%) compared to normal category aircraft. Overall, the weight fraction reduction values for each phase are almost the same.…”

Section: Discussionmentioning

confidence: 99%

Aircraft Performance Simulation of 19-Passenger Commuter Aircraft: A Comparison between Normal and Amphibious Category

Adhitya

2024

JMechE

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This article presents calculating flight performance aspects and simulations of flight characteristics during a flight mission of the 19-passenger commuter aircraft, with a focus on the comparison between the normal and amphibious category aircraft. The objective is to analyse the flight characteristics (warm up, takeoff, cruise, descent, landing) and capabilities of both aircraft configurations. The significant difference between the two aircraft lies in the presence of float components in the 19-passenger Amphibious aircraft. The calculation process, both manual and simulation-based, involves utilizing constraint analysis and mission analysis to determine the weight fraction values for each flight phase. The results of the constraint analysis indicate that the amphibious category aircraft has higher values (35% - 80%) compared to the normal category aircraft. Meanwhile, the calculations using aircraft engine design (AEDsys) software reveal nearly identical reductions in weight fraction for each phase, with the amphibious category aircraft having a significant decrease in the final weight fraction of 0.87836. The fuel weight used is 2129 lb or 965.70 kg (8 barrels) with a range of approximately 372 nm or about 690 km and a flight time of approximately 2.4 hours. The drag polar values obtained using Parametric cycle analysis software at an altitude of 3,048 meters (10,000 ft) show that the normal category aircraft has a smaller coefficient drag (CD) value. Further validation of the findings from this performance simulation study can be conducted through direct experimental validation during flight to be utilized for optimizing aircraft performance.

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“…In terms of FC aircraft, under the MAHEPA project, Marksel et al [9] performed mass estimations for a 19-seater FC aircraft using rapid and semi-empirical methods and estimated the mission fuel at conceptual level of analysis using the Breguet equation combined with electric component efficiencies for the SFC calculation. The authors considered both future optimistic and present pessimistic values for component power densities, efficiencies and other technological factors.…”

Section: Fuel Cell Aircraft Conceptsmentioning

confidence: 99%

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

Pontika

Zaghari

Zhou

et al. 2023

AIAA SCITECH 2023 Forum

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This paper presents the development and application of an integrated, higher-fidelity framework developed within CHARM (the Cranfield Hybrid electric Aircraft Model) for the design, performance analysis and overall evaluation of novel electrified propulsion systems. The developed framework is used to model and analyze the performance characteristics of a Fuel Cell (FC) regional aircraft system in comparison with a conventional regional aircraft and a hydrogen gas turbine regional aircraft retrofit. The FC propulsion system and the hydrogen gas turbine are retrofitted to the same conventional aircraft platform. Physics-based aircraft performance calculations, propeller maps, gas turbine component maps, off-design cycle analysis, electric component maps, calculations for the electric power management and distribution, and a Proton-Exchange Membrane FC (PEMFC) configuration sized to cover the power requirements of a regional aircraft, are integrated within this framework to capture the performance and interaction of components, sub-systems and aircraft during any flight mission and conditions. The aircraft performance, the propulsion system performance characteristics and the emissions of the three technologies are calculated and discussed to understand the challenges and opportunities of using hydrogen-electric propulsion (FC). The effect of capturing the variable mission parameters and flight phases on the performance of the electric power system and FC is presented and compared against a lower fidelity modeling approach for the electric powertrain. The sensitivity of the FC propulsion system and its attributes to varying mission requirements (island-hopping, range, cruise altitude, ambient conditions), as well as the change in the consumed fuel, are demonstrated. This framework can be used to inform the decision-making for the design of electric components and thermal management systems (TMS), and the importance of capturing the trade-off between mass, efficiency and operational constraints in the design process is highlighted. Also, the off-design performance of the electric power system designs and FC is modeled to decide if the design is within acceptable limits under various conditions, and capture the effect of mission requirements and flight conditions on the energy consumption of the overall aircraft system. Finally, a parametric analysis addresses the effect of power density improvement with future technology on the energy per passenger and feasibility of the FC regional aircraft.

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Maximum Take-Off Mass Estimation of a 19-Seat Fuel Cell Aircraft Consuming Liquid Hydrogen

Cited by 8 publications

References 15 publications

Design studies for a light aircraft wing with highly integrated load-bearing hydrogen tanks using multi-objective optimization methods

Design studies for a light aircraft wing with highly integrated load-bearing hydrogen tanks using multi-objective optimization methods

Aircraft Performance Simulation of 19-Passenger Commuter Aircraft: A Comparison between Normal and Amphibious Category

Integrated Mission Performance Analysis of Novel Propulsion Systems: Analysis of a Fuel Cell Regional Aircraft Retrofit

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