Theoretical research and calculations show, that specific original aerodynamic scheme and composites application allow to create an ultra light UAV for universal purpose with a relatively low cost in manufacturing and maintenance. That kind of UAV family may be competitive and it allows to decide many practical problems with good efficiency. To implement this project it is necessary to research many scientific (mainly experimental) and practical problems. Otherwise the project implementation could help perfect experimental base, methods and experience in aerodynamics, composites application and automatic control. The main concept of the UAV project is the creation of an especially light aerial vehicle. It means that all aerodynamic, flight dynamic, strength and structural solutions must be precisely selected in order to minimize the mass of the UAV. Aerodynamic configuration is selected taking into account the largest possible decrease in the mass of the wing. The control system is assumed to be structurally simple. To a certain extent this causes worsening of the maneuverability of the aircraft. One of the most important problems is the selection of materials and structure optimization. The composites intended to be used for the main structure of the UAV are honeycomb or foamed plastic. These kinds of structural solutions are very good at the tension or local bending, but are not effective at the compression of wing structural panels. The problem of buckling and structure optimization is solved by theoretical and experimental methods. Wind tunnel experiments are performed to investigate the propeller and all the power plant. The large scale flying model with remote control is in the stage of production. It will be used for a series of aerodynamic and strength experiments in the process of execution of experimental flights.