Design aspects of flight and navigation systems for small UAVs of different types

The main problems in developing flight and navigation systems for small unmanned aerial vehicles (with the takeoff weight not exceeding 100 kg) and their possible solutions are considered. An example of a flight and navigation system construction for a helicopter-type aerial vehicle is given. The following aspects are considered: hardware implementation of the flight control computer, implementation of the ground control station and aircraft stabilization algorithms. The choice of sensors used to obtain primary information is substantiated. The results of the flight tests are discussed.