THREE PLANE APPROACH FOR 3D TRUE PROPORTIONAL NAVIGATION

Keywords : Missile Guidance, Homing Missiles, 3D True Proportional Navigation

In this thesis; a new three-dimensional (3D) guidance approach is developed. The performance of this approach has been tested visually via developed simulation environment. Although this approach is based on True Proportional Navigation (TPN), it diverges when computing accelerations special to TPN, and putting 3D acceleration commands into practice in Cartesian coordinates. Proposed algorithm works by separating 3D space with axes x, y and z to three perpendicular plane xy, xz and yz respectively; after solving the pursuitevasion problem analytically in these planes and computing required accelerations, rejoining the solutions to three-dimensional environment with respect to the geometric relationships. Trajectory and performance analysis are performed in our simulation software, VEGAS (Visual End-Game Simulation). It is verified that the performance of proposed approach is robust and effective in terms of the miss distance and interception time for the 10-g capacity aerial targets employing evasive maneuvers. The adaptive approach proposed in this thesis can be applied also to the other Proportional Navigation types.