Multi-objective optimization of multi-stage heat sink of electric aircraft using three-dimensional thermal network analysis

The efficiency, reliability, and safety of aircraft have been improved by substituting hydraulic mechanical systems with electric systems. Furthermore, in future aircraft, where fan-driving engines are partially replaced motors, solving the thermal management heat generation from motor-controlling power-devices will become a crucial problem. In this study, three-dimensional steady network analysis (TNA) was carried out to analyze temperature field sink, for motor-controller air cooling, which is expected be used aircraft. numerical procedure verified comparing results TNA those fluid-solid conjugate transfer using finite volume method. After verification, an flight scenario, optimum geometry sink investigated, minimizing following three objective functions: pressure loss flow through maximum local wall at surface motor controller, weight sink. multi-objective optimization, design experiments technique decide space-filling points six parameters. functions each sampling point were calculated TNA. A response created function. optimization on surfaces, genetic algorithm, iteratively find Pareto optimal solutions air-cooled multi-stage From solutions, effects parameters discussed. addition, multiple regression performed quantitative evaluation dominant function identified.