Mission Performance Trade-offs of Battery-powered sUAS

Abstract

A sensitivity analysis is presented on the influence of the weight, altitude and speed of battery-powered sUAS on the resulting stall speed, endurance and range. To aid in the determination of the aircraft performance prior to flight, a method is being brought forth that quantifies the impact of these mission parameters. As a case study the P31015 sUAS is used. The P31015 is a concept model of a battery-powered sUAS with a total battery capacity of 977Wh. Since the aerodynamic model of the aircraft was determined through simulations, and the specific propulsion set-up is yet to be determined, the case study remains to be a theoretical approach. The proposed methods and limitations of this study are applicable to other electric sUAS in similar set-up.