Abstract Following gyro failures in April 2001 and April 2003, HST Pointing Control System engineers designed reduced-gyro control laws to extend the spacecraft science mission. The Two-Gyro Science (TGS) and One-Gyro Science (OGS) control laws were designed and implemented using magnetometers, star trackers, and Fine Guidance Sensors in succession to control vehicle rate about the missing gyro axes. Both TGS and OGS have demonstrated on-orbit pointing stability less than 7 milli-arcseconds, which depends upon the guide star magnitude used by the Fine Guidance Sensor. This paper describes the design, implementation, and on-orbit performance of the HST reduced-gyro control system.
Hubble Space Telescope Reduced-Gyro Control System
The Journal of the Astronautical Sciences ; 57 , 1 ; 419-456
2009-01-01
38 pages
Article (Journal)
Electronic Resource
English
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