Missile Simulation Data and Proportional Navigation Analysis

Using missile simulation data, we can draw significant conclusions about guidance system performance. To better visualize ballistic characteristics, we implemented trajectory plotting algorithms that generate ideal trajectory curves based on numerical simulation data. After establishing a 3D trajectory simulation model for proportional navigation method using differential equations, we conducted comprehensive simulations comparing multiple guidance laws. The simulation framework includes implementations for proportional navigation, incremental proportional navigation, quadratic-based optimal guidance law, and dynamic-characteristic-considered quadratic optimal guidance law. Through these simulation experiments, we obtained the following key findings: - The dynamic-characteristic-considered quadratic optimal guidance law demonstrates superior performance in terms of optimality and stability - Comparative analysis reveals that both incremental proportional navigation and quadratic-based optimal guidance law produce satisfactory trajectory results with proper parameter tuning - We developed encounter time calculation algorithms that precisely determine missile-target interception times, which is crucial for practical applications and system validation The numerical implementation involves solving guidance differential equations using Runge-Kutta methods and tracking missile states through 3D coordinate transformations. The simulation code includes modules for guidance law switching, trajectory data logging, and performance metric calculation. In summary, our in-depth research on proportional navigation methods has identified the most effective guidance law configuration. These findings will significantly contribute to future missile design and manufacturing processes, ultimately enhancing missile precision and operational efficiency through optimized guidance algorithms.