Sequential Processing of Inter-Satellite Doppler Tracking for a Dual-Spacecraft Configuration

The navigation of future interplanetary spacecraft will require an increasing degree autonomy to enhance space system performance. A real-time trajectory determination is paramount importance reduce the risks operations devoted exploration celestial bodies in solar and dependence loading on ground systems. We present a technique for sequential estimation orbits through processing line-of-sight relative velocity measurements that are acquired by novel inter-satellite tracking system. This scheme based extended Kalman filter tested validated realistic Mars mission scenario. Our numerical simulations suggest proposed can provide accuracies few meters position millimeters per second velocity.