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Attitude control/momentum management and payload pointing in advanced space vehiclesThe design and evaluation of an attitude control/momentum management system for highly asymmetric spacecraft configurations are presented. The preliminary development and application of a nonlinear control system design methodology for tracking control of uncertain systems, such as spacecraft payload pointing systems are also presented. Control issues relevant to both linear and nonlinear rigid-body spacecraft dynamics are addressed, whereas any structural flexibilities are not taken into consideration. Results from the first task indicate that certain commonly used simplifications in the equations of motions result in unstable attitude control systems, when used for highly asymmetric spacecraft configurations. An approach is suggested circumventing this problem. Additionally, even though preliminary results from the second task are encouraging, the proposed nonlinear control system design method requires further investigation prior to its application and use as an effective payload pointing system design technique.
Document ID
19910008872
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Parlos, Alexander G. (Texas A&M Univ. College Station, TX, United States)
Jayasuriya, Suhada (Texas A&M Univ. College Station, TX, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1990
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-185644
REPT-90-DISL-05
NAS 1.26:185644
Accession Number
91N18185
Funding Number(s)
CONTRACT_GRANT: NAG9-275
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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