Achievement of high-accuracy indication of deviation of satellite vehicle from orbit plane about vertical by gyrocompassing techniques requires either extremely tight vehicle control or data handling in stabilized coordinates; paper develops mathematical model and error relationships for latter approach; two configurations, vertical and horizontal damping, are described, and it is shown that former emphasizes LF horizon sensor and gyro errors, whereas latter emphasizes their HF characteristics; systematic error due to earth's oblateness, if uncompensated, may be dominant and can produce over 0. 1° of error of satellite altitudes of 250 nautical mi.
Orbital gyrocompass heading reference for satellite vehicles
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 2 , n 6
1965
6 pages
Article (Journal)
English
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Third-order orbital gyrocompass heading reference.
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