Integrated Propulsion System Analysis Framework for Designing Advanced Air Mobility Aircraft

Electric aircraft emerge as a promising solution to mitigate the environmental impact of the aviation sector. The integration of electric propulsion components in such aircraft differs significantly from that of conventional aircraft. In the latter case, initial sizing frameworks typically employ mathematical models that operate solely with high-level propulsion parameters, such as power, thrust, and efficiency. However, in the case of advanced air mobility (AAM) aircraft, the propulsion system integration at the sizing stage is critical to exploring more comprehensive configurations and avoiding infeasible solutions. We introduce a framework for designing AAM aircraft, emphasizing the crucial integration of propulsion components from the initial phase. It combines top-level, low-fidelity methods, higher-fidelity components, and system-level propulsion analysis. This modular approach facilitates realistic aircraft configuration exploration by efficiently balancing high and low-fidelity studies. This integrated approach significantly reduces the risk of infeasible or impractical solutions and allows for adaptable coupling with various models of differing fidelity. We demonstrate the framework’s effectiveness by designing and analyzing a box-wing vertical takeoff and landing electric aircraft. Key results suggest setting the propeller pitch optimally at each mission segment increases the cruising range of aircraft by at least 10%. Similarly, varying the battery cell type with a fixed pack mass results in up to 10 km gain in cruising range for the optimal cruise speed. Propeller pitch, battery cell type, and other parameters are often omitted in the initial sizing stage. Our results emphasize the high sensitivity of aircraft performance to these parameters. The proposed framework illustrates its potential to advance electric aircraft design, contributing to a more sustainable future in aviation.