Horizontal Tail and Aileron Sizing for Distributed Electric Propulsion Aircraft
T. Dundulis (TU Delft - Aerospace Engineering)
R. de Vries – Mentor (TU Delft - Flight Performance and Propulsion)
R Vos – Graduation committee member (TU Delft - Flight Performance and Propulsion)
M. F.M. Hoogreef – Graduation committee member (TU Delft - Flight Performance and Propulsion)
E. Van Kampen – Graduation committee member (TU Delft - Control & Simulation)
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Abstract
The concept of Distributed Electric Propulsion (DEP) aircraft holds great promise in achieving the goals outlined in Flightpath 2050. This involves utilizing electricity to power propellers and enhancing overall flight performance through interactions between the wings and propellers. This thesis investigates the stability and control aspects of DEP aircraft compared to conventional aircraft. A tool is proposed to estimate the minimum horizontal tail and aileron size for different configurations, considering propeller effects. Analyzing three configurations (turboprop excluding propeller effects, turboprop including propeller effects, and DEP including propeller effects), propellers are found to destabilize the aircraft but enhance take-off rotation and provide additional damping during roll. The DEP aircraft exhibits a 19% smaller normalized horizontal tail size than the turboprop (with propeller effects), attributed to lower propeller destabilizing moments and a shorter fuselage. Despite a lower roll requirement, the DEP aircraft needs the same normalized aileron size due to larger rolling moment of inertia. A sensitivity analysis suggests a T-Tail is optimal for DEP aircraft stability, and adjusting battery placement and reserve fuel improves overall performance.