Overcoming unobservability in 3-axis stabilization of satellites
Abstract
An optimal solution is provided to the problem of attitude estimation for a three-axis stabilized satellite devoid of yaw sensor and undergoing significant disturbing torques. Influence of such torques on expectable system performance is analysed via a geometric approach. Estimation of satellite attitude is demonstrated to be systematically impaired by an error resulting from the system's torque-induced unobservability. The said error is then explicitly assessed as a function of the disturbing torques. Furthermore, assuming a priori knowledge of the disturbing torque amplitudes, an optimal observability canonical form is derived. Optimal attitude estimation is finally provided, together with the expression of the relative, thus minimized, systematic error.
- Publication:
-
In AGARD Guidance and Control Tech. for Advan. Space Vehicles 21 p (SEE N84-24603 15-12
- Pub Date:
- January 1984
- Bibcode:
- 1984gcta.agar.....P
- Keywords:
-
- Accuracy;
- Attitude Control;
- Error Analysis;
- Estimates;
- Momentum;
- Synchronous Satellites;
- Torque;
- Algorithms;
- Amplitudes;
- Approximation;
- Axes Of Rotation;
- Nonlinear Equations;
- Optimization;
- Vectors (Mathematics);
- Launch Vehicles and Space Vehicles