Multi-disciplinary design and feasibility study of distributed propulsion systems

This paper discusses pre-design and integration considerations involved when implementing distributed propulsion for future aircraft concepts. In this context, distributed propulsion is achieved by utilization of multiple or a single (large) fan. The distributed integration of the propulsion system leads to strong coupling between airframe aerodynamics and motive power performance, which is addressed with high-end, low-fidelity and interlaced fidelity methods. As a first step, representative integrated and distributed propulsion system configurations were qualitatively evaluated in terms of power system integration, operational aspects, weight, noise, and efficiency. Selection of the distributed propulsion solution for further investigation was based upon identification of the greatest potential to realize quantitatively benefits of boundary layer ingestion at aircraft system level. With regards to the multidisciplinary aircraft-level analysis, input from all relevant technical sub-spaces were examined, and the chosen configuration then compared to an advanced reference aircraft reflecting evolution in the state-of-the-art. Finally, comparative trade studies were performed in order to identify a best and balanced solution for the chosen configuration.