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. (Author)
Overcoming Unobservability in Three-Axis Stabilization of Satellites
1984
21 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Navigation & Guidance System Components , Unmanned Spacecraft , Attitude control systems , Satellite attitude , Space systems , Stabilization systems , Errors , Torque , Gyro stabilizers , Equations of motion , Foreign technology , Component Reports , NATO furnished , Three-axis stabilization