A retrofit analysis on a 90 passengers regional jet aircraft is performed through a multidisciplinary collaborative aircraft design and optimization highlighting the impact on costs and performance. Two different activities are accounted for selecting the best aircraft retrofit solution: a re-engining operation that allows to substitute a conventional power-plant platform with advanced geared turbofan and an on-board-systems architecture modernization, considering different levels of electrification. Besides the variables that are directly dependent from these activities, also scenario variables are considered during the optimization such as the fuel price, the fleet size and the years of utilization of the upgraded systems. The optimization is led by impacts of the retrofitting process on emissions, capital costs and saving costs, computed at industrial level. Overall aircraft design competences (aerodynamics, masses, performance, noise, and emissions) have been computed increasing the level of fidelity and reliability. The whole process is implemented in the framework of the AGILE 4.0 research project in a collaborative remote multidisciplinary approach. Results show that the engine retrofitting can be a profitable solution for both manufacturers and airliners. Conversely, the on-board-system electrification seems to be not convenient in a retrofitting process due to the high capital costs. Depending on the operative scenario, involved stakeholders can properly orient their decision on a retrofitting strategy.

– The work introduces a preliminary design chain valid for hybrid-electric, full-electric, and thermal powered aircraft. From early stages of the design process, the integration of aero-propulsive interaction between propeller (or fan) slipstream and airframe is an important step to obtain trends and compare different aircraft. The present work integrates in the design chain both the distributed propulsion and tip-mounted propeller interactions, deriving for the latter effect a simple model suitable for point performance estimation. The research activity is oriented by market and political demands. Derived from these requirements, two different applications of the design process are proposed on FAR/CS-25 and FAR/CS-23 certified aircraft. Trends about the possible applications, benefits, and drawbacks show that, with the current technology state of the art, a full-electric aircraft is still unfeasible, unless a design range of 100 nmi is acceptable.