This work extends the CNES MATLAB Navigator from Earth-centric to interplanetary operations by enriching its dynamics and measurement toolkit within an Extended Kalman Filter (EKF) that runs over “orbital windows” and is driven by modular inputs, directives, and telecommands. The dynamics now include IAU-compliant inertial and body-fixed frames (ICRF/BCF), TDB time handling, Chebyshev-based ephemerides, third-body gravity (including solid tides where relevant), first-order relativistic terms, a plate-based solar-radiation-pressure model with eclipse logic, and thrust profiles. On the navigation side, the EKF processes optical line-of-sight (LOS) angles and a LiDAR range model for proximity operations; a mission-generation tool in Java produces scenarios, measurements, and reference ephemerides allowing for testing of the navigator in different missions and environments.