Proportional Navigation Guidance 3D Trajectory Simulation for Attacking Horizontally Maneuvering Targets

This research on MATLAB-based 3D trajectory simulation of proportional navigation guidance for attacking horizontally maneuvering targets aims to explore the design and optimization of advanced missile systems. The simulation encompasses multiple disciplines including mathematical modeling, control systems, and dynamics. In this study, we implement a series of algorithms and methods to simulate missile motion during engagements with horizontally maneuvering targets, utilizing proportional navigation guidance laws with 3D kinematic equations. Key MATLAB implementations include target maneuver modeling using state-space equations, guidance law calculation through relative velocity and line-of-sight rate computations, and numerical integration methods (such as Runge-Kutta) for trajectory propagation. Additionally, we investigate missile structural design parameters to enhance accuracy and stability, incorporating aerodynamic coefficient calculations and control system response simulations. The simulation results contribute to improving missile precision and operational efficiency, while providing valuable insights for related research fields in guidance systems and missile technology.