The project established TLARs and technical requirements for a regional aircraft with a FFC-based propulsion system. A base reference architecture was defined, including the logical architecture, func-tional decomposition, and subsystem analysis. Iterative design loops and a Design Dossier document were utilized to develop and validate the system model and interface data.
Furthermore, the test requirements specification for the MMW ground demo was initiated in collabora-tion with the consortium. The supply infrastructure for H2 and N2 was built up at MTU's Munich plant and is currently being prepared for commissioning.
Conceptual development work regarding the Electric Powertrain (EPT) was also initiated. The general gearbox, propeller, and heat exchange system (HXS) design were established.
To explore the design space and identify optimization potential, a series of trade studies were defined and established, and these studies are currently ongoing during the design loop 2, which will continue until the end of 2024.
The baseline design of the Hydrogen Fuel System (HFS) has been concluded, and the detailed design phase has been initiated with the aim of completing the Critical Design Review (CDR) for this system before the end of 2024.
Early in 2025 the preliminary design milestone has been achieved, and the baseline HEROPS MMW design has been defined. Additionally, the first aircraft impact assessment has been established.
Several component and system-level tests are planned and currently underway across various technologies, including EPT, Electrical Distribution System (EDS), HXS, Wind Tunnel Testing (WTT), and Hydrogen Fuel System (HFS), with the objective of reaching Technology Readiness Level 4 by the end of 2025.
