In this paper, an optimal batch estimator and filter based on the Minimum Model Error (MME) approach is developed for three-axis stabilized spacecraft. Three different MME algorithms are developed. The first algorithm estimates the attitude of a spacecraft using rate measurements. The second algorithm estimates the attitude without using rate measurements. The absence of rate data may be a result of intentional design or from unexpected failure of existing gyros. The third algorithm determines input-torque modeling error trajectories. All of the algorithms developed in this paper use attitude sensors (e.g., three-axis magnetometers, sun sensors, star trackers, etc.). Results using these new algorithms indicate that an MME-based approach accurately estimates the attitude, rate, and input torque trajectories of an actual spacecraft.
MME-Based Attitude Estimator Using Vector Observations
1995
15 pages
Report
No indication
English
Astronautics , Spacecraft Trajectories & Flight Mechanics , Algorithms , Attitude (Inclination) , Computer programs , Error analysis , Kinematics , Mathematical models , Random noise , Satellite orientation , State estimation , Statistical analysis , Three axis stabilization , Angular velocity , Attitude control , Boundary value problems , Equations of motion , Estimates , Matrices (Mathematics) , Spacecraft trajectories , State vectors , Torque
An MME-Based Attitude Estimator Using Vector Observations
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