Optimal correction coefficients and selection of optimum star in stellar-inertial guidance systems
Abstract
The use of stellar sensor measurement values to correct for the trajectory parameters of a vehicle is examined. Error sources in stellar-inertial guidance systems are analyzed; a set of optimal correction coefficients which minimize the trajectory deviation is derived. The selection of the optimum star is studied, and methods for determining the region of the optimum star in terms of the bearing and elevation of the star are described.
- Publication:
-
15th International Symposium on Space Technology and Science
- Pub Date:
- 1986
- Bibcode:
- 1986spte.conf.1143Z
- Keywords:
-
- Inertial Guidance;
- Spacecraft Guidance;
- Spacecraft Trajectories;
- Star Trackers;
- Correction;
- Error Analysis;
- Space Communications, Spacecraft Communications, Command and Tracking