Attitude Determination of a Three-Axis Stabilized Spacecraft Using Star Sensors
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Pagination or Media Count:
The purpose of this thesis is to investigate the application of a six-state discrete Kalman filter for estimates of angular rates based solely on star sensor data. The satellite is in a Molnyia orbit where orbital angular velocity and orbital angular acceleration are predetermined and stored in the on-board computer such that they will be available each time a star observation is made. A two-axis star sensor will provide two angles to the estimator whereupon the third unsensed angle will be predicted the rates about all three axes are then estimated. The results show that the rate estimates are accurate to within 10exp -7 rs, which is equivalent to the data produced by gyroscopes.
- Unmanned Spacecraft