A novel cooling solution based on a two-phase pumped cooling system will be developed to cool power electronics in the hybrid/electric propulsion aircraft, where the amount of heat to be dissipated is orders of magnitude larger than conventional aircraft.
- Expected results: Low specific thermal resistance for cooling of power electronics modules with values for the specific, stationary thermal impedance from sink to coolant lower than 1.3*10-4 [K*m2/W], under conditions representing the aircraft thermal environment.
- Success evaluation: Laboratory measurements for the cooling system will be done to verify the achieved values of thermal impedance.
