Characterization of the Aero-Propulsive Performance of a sUAS Paramotor

A commercial-off-the-shelf small unmanned paramotor was analyzed through flight test, computational aerodynamic simulation, and propulsion system modeling. Conventional flight test procedures were adjusted to combat platform-specific challenges. Low-order modeling approaches were adapted for the vehicle and aero-propulsive performance characteristics of lift-to-drag ratio, climb rate, and power required for steady flight were verified. The effect of wing loading on the aerodynamic performance was characterized and approximations for mission-critical attributes of flight duration and range were made. Flight test data and modeling methods are provided as a baseline for future study into sUAS paramotor flight performance and to aid and inform future design. Flight testing successfully captured vehicle performance metrics. Model accuracy was increased for paramotor sUAS through empirical and quantifiable adjustments to fixed-wing analysis methods.