THE USE OF STAR TRACKERS TO DETERMINE THE ATTITUDE OF AN ORBITING VEHICLE,
Abstract
The use of star trackers to determine the attitude of an orbiting vehicle is investigated. The operational procedure is divided into three basic modes, the nominal star acquisition mode, the search mode, and the attitude determination mode. These modes and their various options are discussed in this report. Complete details are given for a deterministic solution and possible sequential filtering solutions are briefly mentioned. Details for these more complicated solutions are left for future studies. The computational aspects of the problem are summarized in terms of the required inputs and outputs and of the mathematical operations to be performed within the computer. Error analyses are provided for most of the operational modes. General equations for the resultant attitude errors are given, as well as specific examples. The error sources considered are ephemeris errors, attitude control system errors, star tracker instrument and mounting errors, and gyro drift mounting errors. Computational errors are not considered. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1967
- Accession Number
- AD0827770
Entities
People
- W. L. Brogan
Organizations
- The Aerospace Corporation