Steps Towards the Validation of the Simplified Automated Approach for a Preliminary Safety Assessment via Scaled Flight Testing

This paper describes the first application of a newly developed safety assessment methodology to the e-Genius-Mod, a scaled flight demonstrator with distributed electric propulsion. The methodology uses existing flight test data to create simplified aerodynamic and propulsion models. In the safety assessment, a spanwise lift distribution and propeller slipstream effect modeling technique is added to model aero-propulsive interactions. To define test conditions to validate models against flight data, the test applies specific failure scenarios and single propulsor failures. The application shows the assessment methodology yields high value in the effect of failure on top-level aircraft performance, where the test commonly shows yaw moment failures to be most impactful. Thus, the

study seeks to predict the effect on aircraft control and performance of a reduced vertical tail size. In a non-tailored configuration, model predictions posit that propulsor failures under high thrust and low speed conditions may fall outside the aircraft's yaw control authority. Additionally, a simplified non-dimensional representation of failure cases is described to enhance understanding. This study advances the preliminary research required for the safety assessment of new aircraft configurations.

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