An MMEbased attitude estimator using vector observations
Abstract
In this paper, an optimal batch estimator and filter based on the Minimum Model Error (MME) approach is developed for threeaxis 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 inputtorque modeling error trajectories. All of the algorithms developed in this paper use attitude sensors (e.g., threeaxis magnetometers, sun sensors, star trackers, etc.). Results using these new algorithms indicate that an MMEbased approach accurately estimates the attitude, rate, and input torque trajectories of an actual spacecraft.
 Publication:

Flight Mechanics/Estimation Theory Symposium 1995
 Pub Date:
 May 1995
 Bibcode:
 1995fmet.symp..137C
 Keywords:

 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;
 Astrodynamics