The Simulation Design of Attitude Control of Cruise Missile Based on Fireworks Algorithm

Attitude control of cruise missiles is a key technology for flight stability and accuracy. This paper establishes an attitude dynamics model and analyzes the attitude changes of cruise missiles during flight. It compares attitude calculation methods using algorithms such as the fourth-order Runge-Kutta, improved Euler method, and second-order Runge-Kutta. The convergence of accuracy is tested using the Fireworks Algorithm, and a dynamic model is established through Simulink simulation to test and analyze long-term stable flight by adjusting time and control parameters. The research results provide new ideas and methods for the attitude control of cruise missiles, with significant theoretical and practical implications. With continuous technological advancements, cruise missiles will play an increasingly important role in both military and civilian fields in the future.