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

Electrified aircraft propulsion enables new designs with fewer emissions. One challenge of electrified architectures is handling the electrical components’ waste heat. This because batteries and other components are sensitive to high temperatures accumulate heat within their structure. In this work, we investigate using a thermoacoustic refrigerator cool battery parallel hybrid single-aisle commercial transport aircraft. refrigeration system powered by from turbofan engine core, whereas conventional consumes electricity or shaft power offtakes. Compared vapor cycle refrigerator, results in greater mission fuel burn pressure losses attributable extraction drive refrigerator. Heat exchangers very low may render beneficial compared certain use cases, such as low-altitude missions.