Computer-aided design of the stability and controllability augmentation system for small UAV

The problem of design of the intellectual attitude control system for small unmanned aerial vehicle is considered. This system is designated for unmanned aerial vehicle stability and controllability augmentation in the manual control mode. This problem is solved via combination of the traditional and robust control, and usage of the model-oriented design approach. The results of design are verified in the processes of multi-stage simulation and experimental flight tests; their interpretation is given.