The aim of this project is to investigate battery integration concepts for the wing of the aircraft, based on a battery energy density of 360 Wh/kg at the pack level in short term and up to 440 Wh/kg in long term. With those assumptions, the aircraft carrying 90 passengers should be able to cover 800 km and later 1000 km (excluding reserves).
Extensive research is required in order to investigate the possible climate benefits of large electric aircraft. Basis is the F9X concept proposed by Elysian. The research required is low-TRL (technology readiness level) and fundamental in nature. Due to early stage of product development, the details of subsystems are not yet known and require a more conceptual analysis.
Aim of this activity:
• To investigate technical feasibility of propulsion system integration into the aircraft and in particular the integration of energy storage system (batteries) inside the wing.
• To provide heavy-weighted battery carrying wing structural concepts with aeroelastic load and mass estimation
In particular, the following questions should be addressed and answered:
• What are the requirements for the battery system integration? In particular the standards and specifications as well as environmental conditions and functional hazard analysis.
• How are the battery cells combined into a packing under consideration of cell design, thermal and power management and mitigation strategies for thermal runaway and propagation?
• What are feasible concepts for battery integration into structural elements of the wing including possible serviceability and maintenance concepts?
• What are critical load scenarios and which effects drive the wing design
“Can a battery pack be designed and integrated in the wing in a way that battery-replacement procedures can be carried out, certification requirements are met, and a pack/cell ratio below 1.25 is achieved?” with sufficient confi-dence.
“Is it possible to design a wing structure carrying heavy batteries and powertrain elements, which can provide the necessary rigidity and withstand all relevant load cases, and does not exceed the weight budget (Includes wing box, skin, LE/TE devices, tip folding, mechanism, landing gear, attach point; excludes, actuators/control systems) of 6150 kg?
