Electrical System Architectures for Future More-Electric Aircraft: Design Strategies and Key Challenges

Kurzfassung

The increasing electrification of on-board systems and propulsion significantly raises the installed electrical power, while advances in power electronics (e.g., SiC, GaN) and battery technologies improve performance but introduce new integration challenges. Furthermore, the shift toward (partially) electrically actuated flight controls imposes higher reliability requirements, and electrified powertrains necessitate operation in much higher power classes. At the system level, major challenges arise from strong interdependencies between components, subsystems, and operational modes. Early architectural decisions critically influence efficiency, weight, reliability, and thermal load. Consequently, a structured design process is essential, beginning with high-level architecture selection, followed by iterative simulation, optimization, and hardware validation. Architectural separation concepts help reduce complexity and improve reliability. The proposed design methodology is demonstrated for both a More-Electric derivative of an A320-class aircraft and a plug-in hybrid battery-electric aircraft, highlighting the need to reassess conventional design assumptions. Key takeaways include the necessity to rethink architectures, which often no longer meet future requirements, and the recognition that weight alone is not the dominant driver. Improved efficiency and reliability can mitigate thermal challenges and thus reduce the thermal system. Ultimately, well-designed electrical system architectures are central to enabling the next generation of electrified aircraft.