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A new momentum management controller for the space stationA new approach to CMG (control moment gyro) momentum management and attitude control of the Space Station is developed. The control algorithm utilizes both the gravity-gradient and gyroscopic torques to seek torque equilibrium attitude in the presence of secular and cyclic disturbances. Depending upon mission requirements, either pitch attitude or pitch-axis CMG momentum can be held constant: yaw attitude and roll-axis CMG momentum can be held constant, while roll attitude and yaw-axis CMG momentum cannot be held constant. As a result, the overall attitude and CMG momentum oscillations caused by cyclic aero-dynamic disturbances are minimized. A state feedback controller with minimal computer storage requirement for gain scheduling is also developed. The overall closed-loop system is stable for + or - 30 percent inertia matrix variations and has more than + or - 10 dB and 45 deg stability margins in each loop.
Document ID
19900020109
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wie, B. (Research Inst. for Advanced Computer Science Moffett Field, CA, United States)
Byun, K. W. (Research Inst. for Advanced Computer Science Moffett Field, CA, United States)
Warren, V. W. (Research Inst. for Advanced Computer Science Moffett Field, CA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1988
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.26:187265
NASA-CR-187265
Accession Number
90N29425
Funding Number(s)
CONTRACT_GRANT: NCC9-16
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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