Thermal Management System Modeling for Preliminary Design of Fuel Cell-Based Aircraft

Habrard, Valentine; Pommier-Budinger, Valérie; Hazyuk, Ion; Jézégou, Joël; Bénard, Emmanuel

doi:10.2514/6.2023-4303

Cited by 1 publication

(3 citation statements)

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“…Once, these requirements are defined, the HEXs are iteratively sized to ensure the correct heat transfer area. The other components are modeled as in [2]. The TMS component models do not include the power and water management of the fuel cell system, neither the humidifier for the air supply system.…”

Section: Sizing and Fuel Mass Penaltymentioning

confidence: 99%

“…A fuel cell liquid-cooling TMS has been previously developed for a hybrid aircraft case study [2]. The objective of this work is to perform a comprehensive system analysis, which includes optimizing the system with respect to a given objective, and conducting a sensitivity analysis on the different input parameters and model assumptions.…”

Section: Introductionmentioning

confidence: 99%

“…These choices are justified by the low temperature PEMFC's maturity and the KFO's large temperature range between freezing and boiling points. The complete list of initial assumptions for the TMS and components' efficiencies is given in [2].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Sensitivity Analysis and Optimization of a Liquid Cooling Thermal Management System for Hybrid Fuel Cell Aircraft

Habrard,

Hazyuk,

Pommier-Budinger

et al. 2024

J. Phys.: Conf. Ser.

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The objective of this work is to perform a comprehensive system analysis of a liquid-cooling thermal management system for a hybrid-electric aircraft using fuel cells for general aviation by sizing and optimizing the system with respect to a given objective. A sensitivity analysis on the different design parameters and model assumptions is also performed and their impact on the aircraft and its performances will be assessed. Firstly, the case study is defined and an optimization is run with some initial assumptions leading to a feasibility study for the implementation of this system. The sensitivity analysis is then undergone for the chosen coolant type and fuel cell stack temperature selected after the first optimization. Incorporating the findings of this analysis, a second optimization is run on the thermal management system with improved inputs in order to demonstrate a scenario with reduced penalty on the aircraft. Preliminary results show that implementing this hybrid propulsion system along with its thermal management is feasible with a reduction in payload and range. In addition, it can be concluded that initial assumptions and design choices are shown to have a significant impact on the system’s sizing and should be considered in aircraft sizing design loops.

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Section: Sizing and Fuel Mass Penaltymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%