An operational algorithm for satellite attitude determination from GPS carrier phase

This paper presents an operational approach for determining satellite attitude from carrier phase GPS (Global Positioning System) measurements. A conventional recursive least square (RLS) estimator was implemented without requiring spacecraft dynamics. The proposed approach can be applicable for general space missions, particularly for real-time operation onboard-spacecraft. The attitude angles and electrical path difference (line bias) between antenna chains caused an offset error in GPS observables, can be estimated. The implemented estimator was tested with a simulated data, and the flight data collected onboard a mini-satellite orbiting in low Earth orbit.