Ascent Trajectory Optimization Design of Solid Launch Vehicle Based on Newton Iteration Method

In this paper, a trajectory optimization design method based on solid launch vehicle ascent phase trajectory is proposed. We have created a Newton Iteration Method for the best possible trajectory track design and a trajectory program for the vehicle's active stage. The Newton Iteration Method algorithm successfully handles solid rocket trajectory optimization design issues, as shown by analysis and simulation results. It satisfies requirements for separation point inclination, height, and other parameters while optimizing the trajectory path scheme in the ascending trajectory. The technique improves convergence stability and speed, making engineering implementation easier. This work provides a theoretical framework for ascent trajectory optimization design and offers valuable insights for practitioners in the field.