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Attitude control system conceptual design for the GOES-N spacecraft seriesThe attitude determination sensing and processing of the system are considered, and inertial reference units, star trackers, and beacons and landmarks are discussed as well as an extended Kalman filter and expected attitude-determination performance. The baseline controller is overviewed, and a spacecraft motion compensation (SMC) algorithm, disturbance environment, and SMC performance expectations are covered. Detailed simulation results are presented, and emphasis is placed on dynamic models, attitude estimation and control, and SMC disturbance accommmodation. It is shown that the attitude control system employing gyro/star tracker sensing and active three-axis control with reaction wheels is capable of maintaining attitude errors of 1.7 microrad or less on all axes in the absence of attitude disturbances, and that the sensor line-of-sight pointing errors can be reduced to 0.1 microrad by SMC.
Document ID
19910065151
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Markley, F. L.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Bauer, F. H.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Deily, J. J.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Femiano, M. D.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 91-2832
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference
Location: New Orleans, LA
Country: United States
Start Date: August 12, 1991
End Date: August 14, 1991
Accession Number
91A49774
Distribution Limits
Public
Copyright
Other

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