An MME-based 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 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.
- 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