DYNAMIC NAVIGATOR FOR UAV

The present project aims to the analyses and model the auto-navigation process. Putting mathematical model for aeroplane autonavigation requires an understanding to the aeroplane mobility in atmosphere,
and its relationship with the control surfaces in the aeroplane.After the accomplishment of the analysis and modeling, an auto-navigation control system was designed by using the devloped model.The developed control system is oriented to be a navigator to auto-control the aeroplane. In addition to the establishment of navigation programs,a graphical user interface was developed  to display the state of
the aeroplane. Hence the observer would have a chance to monitor the events which the aeroplane may undergo during its flight. In order to test the accuracy of the navigator’s performance, a simulation model was developed and impelemented with the aid of the actual input data the simulator was utilized to investigate the navigator’s response.The encourageing results of the simulator paved the way to start
improving the conducted work. An adaptive method had been suggested,so that the response of the aeroplane become dynamic instead of the static response which is already present. The dynamic response was curried out by two automatic methods which both depend on the amount of deviation between the actual airplane response and the planned response. The results of the dynamic response were more accebtable. The next accomplished step was modeling and simulating the external effects that would influence the performance of the aeroplane in the atmosphere. By studying the wind effect on the aeroplane’s performance during its flight,and analyzing the aerodynamic forces that would deviate the aeroplane