Hybrid and electric propulsion systems for aeronautics represent an enormous potential for innovation, especially with regard to CO2 savings. In order to achieve a reliable, efficient and safe operation of such battery systems, they must be optimized in terms of energy storage capacity, electrical power, total mass and volume, Thermal requirements for materials and construction.
The main goal is to design and assemble a prototype of an entire battery pack with state-of-the-art energy density. A clear definition of the interfaces will insure the easy integration of the demonstrator into current aircraft architectures. The prototype will be developed to reach TRL4 and will be validated in laboratory conditions.