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Single step optimization strategies for constrained retargeting maneuversThe present consideration of recent advancements in the nonlinear guidance of spacecraft, using feedback linearization and decoupling to generate exact nominal commands, gives attention to the correction of saturation effects and oscillation prevention in saturated operating regimes. In the case of spacecraft maneuvered by momentum-transfer devices, real time command generation is possible by means of pointwise minimization of the sum of the squares of the norms of the 'next state error' for the equivalent system and the linear system input. It is also possible to track a nominal trajectory, such as a critically damped harmonic oscillator response, by minimizing the square of the norm of the error between the actual and the tracked states.
Document ID
19860054772
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dwyer, T. A. W., III
(Illinois, University Urbana, United States)
Fadali, M. S.
(Nevada, University Reno, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
86A39510
Funding Number(s)
CONTRACT_GRANT: NSF ECS-83-04968
CONTRACT_GRANT: NAG1-436
Distribution Limits
Public
Copyright
Other

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