Conceptual functional design of hybrid energy source of unmanned convertiplane

Abstract Convertiplane is explored in this article as an unmanned aerial vehicle incorporating hybrid power sources and hybrid propulsion systems. Based on the use of an electric generator in conjunction with a battery, fuel element and internal combustion engine as a source of energy in the non-manifold electrical engine convertiplanes, hybrid power sources and hybrid propulsion systems manufacturing specifications, as well as providing convertiplane with a long-term flight issues are considered hereby. In order to provide selection of the optimal design, hybrid energy source models from connection designs of different types of energy sources have been analyzed. Structural schemes of power systems with different configurations consisting of “sequential”, “parallel” and “mixed” connections of hybrid energy sources and hybrid propulsion systems have been analyzed and optimal connection schemes have been determined on their basis. It has been shown that when using four hybrid winged-motor group, the lifting system becomes complicated, the weight of the convertiplane is becoming relatively heavy. For an airplane weighing 15-20 kg, it is recommended to use four electric motors as a lifting engine, an internal combustion engine as a driving motor and an electric generator to charge the battery during the flight in order to ensure vertical flight, endurance or hovering at the height. A conceptual block diagram of a convertiplane type unmanned aerial vehicle is developed.