الفهرس 
AbstractOnly 14 pages are availabe for public view
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Abstract
In this thesis we will discuss one of the most important scientific branches , guidance and control field which is used in several applications of unmanned aerial vehicles that is widely used in both military and civilian fields in past attempts in establishing the state of the art in spacecraft attitude control have concentrated on cataloguing various satellites in terms of their mission objectives and design features, or on describing specific hardware developments. The discussions in this thesis are developed along the lines of ”what is common” rather than ”what is different” with the idea that seemingly unrelated efforts in this new technology can ”be put in their proper perspective, and that some unresolved problems can be defined. To achieve this objective, first the control system requirements (from a performance rather than a mission point of view) and the implications of such requirements in terms of control system design are discussed. Second, specific attitude control approaches and the associated performance or implementation problems, or both, are considered in ”Conceptual Design,” and some of the theoretical problems are discussed in ”Analytical Design.” Finally, we will analyze and simulate aerial unmanned vehicle trajectory, which have proven its usefulness in the military and civilian applications in recent years .The kinematic three degree of freedom [3DOF] equations of motion for the aerial unmanned vehicle is proofed using pure pursuit guidance method which is known as path planning algorithm. To solve the equations of motion, the numerical integration is used by applying Euler method. The pure pursuit guidance method was stretched well beyond its intended usage by many aerospace applications. The pure pursuit algorithm is used to accomplish goal seeking and path tracking. An analysis and flight trajectory simulation for the aerial unmanned vehicle is given based on constructing MATLAB program describing both rotational and transition motion with the total time of flight .