Design Of Wind Tunnel Rig For The Test Of A Single Electrical Lift Thrust Unit During Conversion Maneuver

Abstract

The aeronautical community is increasingly focusing on innovative multi-propeller electric Vertical Take-Off and Landing aircraft for Advanced Air Mobility. This paper presents the development and validation of methodologies and tools to support the early-stage design of such aircraft. In particular, it focuses on the design of an experimental wind tunnel test rig featuring an electric Lift-Thrust Unit (eLTU) equipped with a tilting mechanism that enables smooth transition between helicopter (H/C) mode and airplane (A/P) mode and independent control of the rotor speed. The test rig integrates a load cell and strain gauges to measure the loads generated by the eLTU under various flight conditions, as well as encoders to track the motion of the tilting mechanism. A numerical aeroelastic model has been developed to guide the rig design and to analyze the coupled aerodynamic and structural behavior of the eLTU and tilting system. Preliminary correlation results from tests conducted without wind are presented, demonstrating the robustness and reliability of the experimental setup in preparation for future wind tunnel campaigns.