Thermal Management System Optimization for a Parallel Hybrid Aircraft Considering Mission Fuel Burn

Adler, Eytan J.; Brelje, Benjamin J.; Martins, Joaquim R. R. A.

doi:10.3390/aerospace9050243

Cited by 16 publications

(4 citation statements)

References 32 publications

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“…The OpenConcept library has a variety of different size aircraft models available as well as series hybridelectric and parallel hybrid-electric modelling capabilities (Adler et al, 2022;Fouda et al, 2022). It is important to note that the weight estimation calculations are based on textbook calculations using empirical formulas (Raymer, 2018;Roskam, 2019;Torenbeek, 2013) and different calculations are implemented based on the aircraft class considered.…”

Section: Aircraft Conceptual Design Frameworkmentioning

confidence: 99%

In-Depth System-Level Energy Analysis of Hybrid Electrified Commuter Aircraft for Improved Energy Efficiency

Diamantidou,

Zaccaria,

Kalfas

2023

Linköping Electronic Conference Proceedings

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This work presents a comprehensive analysis of hybrid electric propulsion systems in commuter aircraft, aimed at enhancing energy efficiency. The study utilizes an aircraft conceptual design library, OpenConcept, to perform evaluations of various aircraft components and their interrelationships. The methodology integrates aerodynamics, propulsion, and mission analysis within a common framework to optimize the aircraft design. The analysis focuses on a 19-passenger commuter aircraft, employing a series/parallel hybrid-electric architecture. The gradient-based Sequential Least Squares Programming optimizer is utilized to optimize design variables such as battery weight, engine power, and the selected power ratios, while adhering to operational constraints. Through a rigorous Design of Experiments study, the paper highlights that even when considering the current battery technology, hybrid-electric propulsion yields substantial energy savings for short-haul missions. The fuel and energy consumption reductions are evident, particularly for shorter ranges. However, for extended missions, the critical role of advanced battery energy density is emphasized to achieve significant energy efficiency improvements.

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Section: Aircraft Conceptual Design Frameworkmentioning

confidence: 99%

In-Depth System-Level Energy Analysis of Hybrid Electrified Commuter Aircraft for Improved Energy Efficiency

Diamantidou,

Zaccaria,

Kalfas

2023

Linköping Electronic Conference Proceedings

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“…The main design challenge to improve the overall TMS performance is how to create such a system wherein the heat loads are the mostly efficiently transported through cooling loops and dissipated at the existing heat sinks. Table 1 sums up some of the most important studies on the TMS integration conducted recently [16][17][18][19][20][21][22][23][24][25]. These studies suggest that liquid cooling, RA cooling, outer mould line cooling, heat exchangers, and the use of fuel as a heat sink are the most promising heat transfer systems, although VCS usage is also explored.…”

Section: Overview Of Tms Architecturesmentioning

confidence: 99%

“…Secondly, life cycle carbon emissions can be reduced [26]. RA, liquid, and VCS [25] The focus of this paper, developed under the scope of the FutPrInt50 project, was mainly two-fold: (i) to develop TMS models that can be incorporated into the conceptual design of the next generation of hybrid-electric regional airliners at a low computational cost to enable multidisciplinary design optimisation; and (ii) to provide a comparison between the different TMS architectures considered in the aforementioned project. These models were conceived and implemented from the scratch for regional hybrid-electric aircraft.…”

Section: Overview Of Tms Architecturesmentioning

confidence: 99%

A Study on Thermal Management Systems for Hybrid–Electric Aircraft

Coutinho,

Afonso,

Souza

et al. 2023

Aerospace

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The electrification of an aircraft’s propulsive system is identified as a potential solution towards a lower carbon footprint in the aviation industry. One of the effects of increased electrification is the generation of a large amount of waste heat that needs to be removed. As high-power systems must be cooled to avoid performance deterioration such as battery thermal runaway, a suitable thermal management system is required to regulate the temperature of the powertrain components. With this in mind, the main objective of this research is to identify promising heat transfer technologies to be integrated into a thermal management system (TMS) such that power, mass, and drag can be minimised for a parallel hybrid–electric regional aircraft in the context of the EU-funded FutPrInt50 project. Five different TMS architectures are modelled using the Matlab/Simulink environment based on thermodynamic principles, heat transfer fundamentals, and fluid flow equations. The systems are a combination of a closed-loop liquid cooling integrated with different heat dissipation components, namely ram air heat exchanger, skin heat exchanger, and fuel. Their cooling capacity and overall aircraft performance penalties under different flight conditions are estimated and compared to each other. Then, a parametric study is conducted, followed by a multi-objective optimisation analysis with the aim of minimising the TMS impact. As expected, none of the investigated architectures exhibit an ideal performance across the range of the studied metrics. The research revealed that, while planning the TMS for future hybrid–electric aircraft, alternative architectures will have to be developed and studied in light of the power requirements.

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“…Furthermore, performance improvement leads to an increase in the number and power of onboard equipment, which in turn causes continuous heating of the aircraft's internal environment [9][10][11][12][13][14]. In this scenario, the fuel thermal management systems (TMSs) within the integrated aircraft TMS play a pivotal role in managing thermal load transfer between the aircraft and engine [15,16].…”

Section: Introductionmentioning

confidence: 99%

Optimization Research on the Heat Transfer Capacity of an Aircraft Fuel Thermal Management System

Zhang,

Lin,

Guo

et al. 2023

Aerospace

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The thermal management system (TMS) for aircraft fuel is a critical component of integrated TMSs in aircraft. As such, its optimal design is necessary to ensure the efficient completion of flight missions. This study presents the model building of a numerical simulation model for the fuel TMS, with the objective of minimizing fuel return flow. Sensitivity analysis was performed using variance analysis. The genetic algorithm was utilized for the optimization of the model building, taking into consideration the system’s geometric structure and performance parameters, which include the pipe length, the ram air-fuel HX’s efficiency, and the ram air’s volume flow rate in the ram air cooling subsystem, as design variables. The optimization solution for system design variables yielded a design scheme with the highest working efficiency for the fuel TMS. In this paper, the genetic algorithm in AMEsim software is adopted, which can also effectively optimize the design parameters and achieve the optimization objective. Compared with the original TMS structure, the heat dissipation capacity of the fuel TMS is improved and reduced the return fuel flow by 67.4% after the optimization of system structure parameters.

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Thermal Management System Optimization for a Parallel Hybrid Aircraft Considering Mission Fuel Burn

Cited by 16 publications

References 32 publications

In-Depth System-Level Energy Analysis of Hybrid Electrified Commuter Aircraft for Improved Energy Efficiency

In-Depth System-Level Energy Analysis of Hybrid Electrified Commuter Aircraft for Improved Energy Efficiency

A Study on Thermal Management Systems for Hybrid–Electric Aircraft

Optimization Research on the Heat Transfer Capacity of an Aircraft Fuel Thermal Management System

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