Diseño de sistemas de propulsión distribuida con ingestión de capa límite para una aeronave no tripulada de fuselaje integrado

Abstract

This work presents the design of propulsion system configurations for a Blended Wing Body (BWB) - Unmanned Aerial Vehicle (UAV), integrating Boundary Layer Ingestion (BLI), Distributed Propulsion (DP) and Thrust Split (TS). The design process has been carried out at a preliminary design stage using parametric models. A study of the integration of BLI, DP, and TS into the design of novel propulsion system configurations is done. According to NASA (National Aeronautics and Space Administration), boundary layer ingestion and distributed propulsion are new technologies that will reduce emissions and noise from aviation sector. Therefore, these technologies will have to be implemented in new aircraft design. The main design parameters are: number of engines for distribute propulsion and boundary layer ingestion percentage. It has been evaluated the variation on propulsion system weight, Take-Off Gross Weight (TOGW), and the static longitudinal stability characteristics for sixty propulsion system configurations. To select the optimal propulsion system configurations, two selection criteria are considered: maximum reduction on TOGW weight, and minimum change on center of gravity location. The results show TOGW can be reduced up to 10% due the integration of BLI, DP, and TS on propulsion system design for blended wing body unmanned aerial vehicles.