Trajectory Analysis of Rockets Using Pseudorange and Terrain-Aided Navigation with Non-Additive Extended Kalman and Particle Filter

This research analyzes the navigation of a symmetric-axis sounding rocket using a 6 Degrees of Freedom (6DOF) simulator and stochastic filters such as the classical Extended Kalman Filter (EKF) and the Particle Filter (PF) to estimate its position, velocity, and attitude. The results compare the effect of a pseudorange-based model using GNSS data to provide accurate position measurements relative to visible satellites.