Missile Trajectory Simulation Calculation

This missile trajectory simulation program employs the fourth-order Runge-Kutta method, a highly accurate numerical solution technique that offers an effective and reliable computational approach for missile trajectory simulation research. The fourth-order Runge-Kutta method operates as an iterative computational algorithm that transforms differential equations into recursive equations. It decomposes large intervals into multiple smaller subintervals, performs calculations within each subinterval, and then combines the results to obtain the final solution, thereby achieving comprehensive missile trajectory simulation. In code implementation, this method typically involves four slope calculations per time step (k1, k2, k3, k4) to achieve higher accuracy. The algorithm's key advantage lies in its self-starting capability and balanced computational efficiency. The method demonstrates high precision, fast convergence rates, and excellent suitability for complex nonlinear systems, making it widely adopted in missile trajectory simulation applications. The implementation usually requires defining state variables (position, velocity, attitude) and governing equations representing aerodynamic forces, propulsion, and gravitational effects.