Development of the Genii-UAS Demonstrator: a Small-Class Vehicle with Low Wing Loading and Fuel Cell Propulsion

摘要

A sub 25 kg class unmanned aerial system has been developed with the intent of flying with power derived from alternative energy systems. The aircraft has a wingspan of 5.5 m; its expected top speed is 23 m/s, maximum takeoff weight is 25 kg, and minimum takeoff distance is 87 m. This paper is focused on the aircraft design and performance calculations. An overview is also given on the aircraft's construction technique and design of the hybrid drive train to incorporate alternative energy systems. Results of simplified design techniques for the aircraft performance are compared with numerical modeling for the wing lift coefficient and induced drag. Limited performance data of the initial flight with battery power is presented. Plans for future testing with gaseous and liquid hydrogen through a PEM fuel cell, and gasoline-electric generator are discussed.