Electro-thermal Models and Design Approach for High Specific Power Electric Motor for Hybrid Aircraft

This paper presents electro-thermal models for sizing the electric motors with their cooling system for Hybrid Aircraft Propulsion. A design approach is proposed to reach high specific powers. An electric motor is sized using tools based on loadability concepts. Its performances are validated by Finite Element Analysis. Cooling system is sized based on adapted hydraulic calculations and temperatures are verified using Lumped Parameter Thermal Model.