Preliminary study for the integrated design of an electro-mechanical wing de-icing system

This paper presents the preliminary design of an electro-mechanical de-icing system for avionic applications. The project belongs in the framework of a broader effort, in the power electronics and aerospace communities, to re-think and redesign many functionalities towards a More Electric Aircraft and, in particular, a more efficient one. Due to very stringent requirements in terms of performance, size and weight and, above all, reliability, the design is strongly characterized by a tight interdependence of functional and structural aspects and its finalization will require in-depth and extensive analysis and testing, taking into account functional performance (e.g., efficiency, EMC), environmental constraints (e.g., pressure, temperature, humidity), mechanical stress (e.g., vibrations) and abnormal events (e.g., radiation, lightning). Here, a first concept for the implementation of the required functionality is presented, along with preliminary functional test results. Main design constraints are also considered and discussed, particularly in terms of system integration and reliability.