Spacecraft attitude pointing performance during orbit adjust as a function of compensator order
Abstract
A steady state compensator of specified order is proposed to estimate the required duty cycle needed to balance the distribution torque. The compensator was increased gradually to demonstrate the improvement in pointing accuracy. The basic mathematical model of the flexible spacecraft and sensor used to characterize the performance of the compensator are described.
- Publication:
-
In NASA. Goddard Space Flight Center Sixth Ann. Flight Mech./Estimation Theory Symp. 4 p (SEE N82-10064 01-12
- Pub Date:
- October 1981
- Bibcode:
- 1981fmet.symp.....B
- Keywords:
-
- Attitude Control;
- Compensators;
- Pointing Control Systems;
- Spacecraft Control;
- Torque;
- Communication Satellites;
- Flight Mechanics;
- Mathematical Models;
- Launch Vehicles and Space Vehicles