Fixed Wing Aircraft Collision Avoidance Using Collision Cone Theory
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Date
2022-08-12Author
Beary, Andrew T. III
0000-0002-3095-2542
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This thesis develops the guidance and control components of an aircraft collision avoidance system, using a collision cone-based approach. These guidance and control laws are developed by considering the nonlinear relative kinematic equations of the aircraft that are on a collision course, as well as the nonlinear flight dynamics of the aircraft performing the collision avoidance maneuver. The longitudinal and lateral-directional axes of the aircraft are considered separately. The developed guidance and control laws are subsequently integrated with the nonlinear aircraft dynamics in a MATLAB/Simulink framework, and simulations performed to demonstrate the working of the overall system.