DEVELOPMENT OF A HYBRID FIXED-WING VTOL UNMANNED AERIAL VEHICLE

Abstract

As the use of unmanned aerial vehicles (UAV) in the world has expanded, the market needs for the development of multi-role unmanned systems are increasing. These unmanned systems tend to largely find their constant and irreplaceable role in many industries. The development of such systems is a complex process, which, among other things, must include detailed structural, static and dynamic calculations and testing. The UAV presented in this paper is a hybrid powered aircraft with vertical take-off and landing (VTOL) with a composite structure and an innovative hybrid propulsion with a starter-generator system. VTOL gives an advantage in the exploitation of the aircraft itself, because it does not require special ground conditions or space for take-off and landing. The starter and generator system enables a smaller amount of fixed mass, such as batteries, while the structure made of composite materials enables a smaller mass and the desired characteristics of strength, resistance to corrosion and fatigue. This paper present development review process of the latest technology in terms of the concept of system and subsystem operation, as well as financially favorable and high-quality construction.