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Application of precomputed control laws in a reconfigurable aircraft flight control systemA self-repairing flight control system concept in which the control law is reconfigured after actuator and/or control surface damage to preserve stability and pilot command tracking is described. A key feature of the controller is reconfigurable multivariable feedback. The feedback gains are designed off-line and scheduled as a function of the aircraft control impairment status so that reconfiguration is performed simply by updating the gain schedule after detection of an impairment. A novel aspect of the gain schedule design procedure is that the schedule is calculated using a linear quadratic optimization-based simultaneous stabilization algorithm in which the scheduled gain is constrained to stabilize a collection of plant models representing the aircraft in various control failure modes. A description and numerical evaluation of a controller design for a model of a statically unstable high-performance aircraft are given.
Document ID
19890049560
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Moerder, Daniel D.
(NASA Langley Research Center; Information and Control Systems, Inc. Hampton, VA, United States)
Halyo, Nesim
(Information and Control Systems, Inc. Hampton, VA, United States)
Broussard, John R.
(Texas Instruments, Inc. Lewisville, United States)
Caglayan, Alper K.
(Charles River Analytics, Inc. Cambridge, MA, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1989
Publication Information
Publication: Journal of Guidance, Control, and Dynamics
Volume: 12
ISSN: 0731-5090
Subject Category
Aircraft Stability And Control
Accession Number
89A36931
Funding Number(s)
CONTRACT_GRANT: F33615-84-C-3608
Distribution Limits
Public
Copyright
Other

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