Thermal management system models for overall aircraft design

Planès, Thomas; Habrard, Valentine; Delbecq, Scott; Pommier-Budinger, Valérie; Bénard, Emmanuel

doi:10.2514/6.2021-2428

Cited by 6 publications

(6 citation statements)

References 16 publications

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“…The total drag, mass and power required by the TMS can be calculated, as well as an additional kerosene fuel mass penalty ∆M f term to consider the effect of adding such a subsystem on an aircraft. This is explained in more detail in [5].…”

Section: Sizing and Fuel Mass Penaltymentioning

confidence: 99%

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%

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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“…In the following, some examples are presented for modeling the drag, pressure recovery, and mass of air inlets. Detailed models can be found in [38,39].…”

Section: Air Inletsmentioning

confidence: 99%

“…The scaling laws can be used to study the effects of a geometric change on the characteristics of a "custom-made" component compared to an existing reference component. For air inlet, its mass M ai can be estimated as a function of the mass flow rate ṁ, using Equation (19) proposed in [38], assuming the geometry and the flow characteristics are conserved. Here, the reference mass of the air inlet, for a reference mass flow rate ṁref = 0.5 kg/s, is assumed to be M f l,ref = 40 kg.…”

Section: Massmentioning

confidence: 99%

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Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

et al. 2023

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The aircraft environmental control system (ECS) is the second-highest fuel consumer system, behind the propulsion system. To reduce fuel consumption, one research direction intends to replace conventional aircraft with more electric aircraft. Thus, new electric architectures have to be designed for each system, such as for the ECS. In this paper, an electric ECS is modeled and then sized and optimized for different sizing scenarios with the aim of minimizing fuel consumption at the aircraft level. For the system and for each component, such as air inlets and heat exchangers, parametric models are developed to allow the prediction of relevant characteristics. These models, developed in order to be adapted to aircraft design issues, are of different types, such as scaling laws and surrogate models. They are then assembled to build a preliminary sizing procedure for the ECS by using a multidisciplinary design analysis and optimization (MDAO) formulation. Results show that the ECS design is highly dependent on the sizing scenario considered. An approach to size the ECS globally with respect to all the sizing scenarios leads to an ECS that accounts for around 200 N of drag, 190 kW of electric power, and 1500 kg of mass for the CeRAS aircraft.

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“…For each of them, models are established to estimate their mass, their possible additional drag, and their contribution to electrical consumption, which are key outputs for overall aircraft design. Air-source heat pump and flush inlet systems were found to be the solutions that cause the least fuel penalty [6].…”

mentioning

confidence: 99%

A Study in Aircraft Heating System Trainer Model AS-43 for Aeronautical Engineering Students Practice

Pisal,

Nor Salim

2023

PAAT

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The Model AS-43 heating system trainer is a fully operational model of a light aircraft heating system demonstrating the combustion air heater method. Heat transfer is related to the mechanism that happens in this process. This study aims to utilize the trainer Model AS-43 for practical experiments in aeronautical engineering education. The research objectives include developing standard operating procedures, determining system parameters, and proposing improvements. The significance of the study lies in enhancing the teaching scope for aeronautical engineering students and improving the aircraft heating system trainer Model AS-43. The obtained results and calculations serve as valuable data for aeronautical engineering education and can facilitate further analysis and improvements in the field. Recommendations are made to enhance the trainer's utilization, including incorporating appropriate measuring tools. Implementing these recommendations would maximize the trainer's educational potential, allowing it to be utilized as an effective teaching tool for mechanical and aeronautical engineering courses. The proposed changes could improve students' comprehension, promoting better learning outcomes and advancing aviation education.

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Thermal management system models for overall aircraft design

Cited by 6 publications

References 16 publications

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

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

Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

A Study in Aircraft Heating System Trainer Model AS-43 for Aeronautical Engineering Students Practice

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