Aeroelastic Investigation of a Regional Aircraft Configuration with Distributed Propulsion and Wing-Integrated Batteries

Kurzfassung

An electric aircraft was derived from a regional hybrid electric aircraft configuration, with reasonable assumptions being made for the volumetric and gravimetric energy density, and for the propulsion and system efficiencies. In order to achieve an acceptable battery mass for the electric aircraft, a reduction of the design mission from 1000 NM to 300 NM was implemented, alongside the utilization of a range-extender with reserve fuel for the reserve mission and a reduction of the number of passengers from 70 to 36. A parameter study was conducted on the integration concept of the battery, investigating the effects of its implementation in the wing box or nacelles on the loads. In addition to the maneuver and dynamic 1-cos gust loads, ground and landing loads were also considered, taking into account the reaction forces on the wing due to battery integration. The DLR's cpacs-MONA process was utilized in this instance to ensure consistency. The loads analysis demonstrates that the integration of batteries within the nacelle results in a substantial reduction in the max. bending moment. The strategic placement of heavy masses along the wing has the potential to reduce loads. However, this must be optimized.