Publication Date:
2019-07-13
Description:
A modified earth horizon sensor design is proposed for the Mars Observer mission. The horizon sensor modification are based on Mars horizon radiance profiles. Attention is given to the Mars Observer's attitude control system, whose primary mode is horizon sensor-based and therefore obviates the use of an onboard spacecraft ephemeris; control accuracy of the order of 10 mrad 3sigma/axis is achieved. The attitude control system's second, celestial-backup mode, wich requires greater operational effort, employs an onboard celestial sensor as the spacecraft ephemeris; its control accuracy is of the order of 8 mrad 3sigma/axis.
Keywords:
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AAS PAPER 86-287
,
Aerospace century XXI: Space flight technologies; Oct 26, 1986 - Oct 29, 1986; Boulder, CO; United States
Format:
text
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