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Title
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The Design of Stability Augmentation Systems for Decoupling Aircraft Responses
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Date
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1972
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Index Abstract
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Coming Soon
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Photo Quality
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Not Needed
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Report Number
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AFFDL TR 72-63
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Corporate Author
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Air Force Flight Dynamics Laboratory
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Laboratory
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Air Force Flight Dynamics Laboratory
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Extent
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152
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Identifier
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AD0747017
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Access Rights
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Approved for public release; distribution unlimited
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Distribution Classification
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1
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Contract
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Laboratory Research - No Contract
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DoD Project
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8219
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DoD Task
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821904
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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None
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Abstract
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Tactical aircraft with STOL capability exhibit undesirable coupled response during the landing phase of flight. A simplified method for designing a stability augmentation system which eliminates the coupling effects is demonstrated. The method is based on Gilbert's decoupling theory which utilizes a feedback control law to obtain a set of single input, single output subsystems. The augmentation system can be designed to provide either command rate or command angle authority in the three rotational axes. Analyses is facilitated through the use of two computer programs, the first of which determines the class of control laws which will decouple a system. The second computer program determines, through transient response analysis, the values of the transfer function parameters required to satisfy response criteria. The results of a piloted simulation which analyzed several decoupled configurations is also presented.
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Report Availability
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Full text available
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Date Issued
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1972-06
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Is Referenced By
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Destuynder, Phillippe & Caroline Fabre, "Few Theoretical Remarks on the Dynamical Control of Racing Sailboats with Foils", Lecture 12: Example of home work on an America Cup, Conservatoire national des arts et métiers (CNAM), 2016
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Provenance
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AFRL/VACA
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Type
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report
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Format
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1 online resource
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Creator
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Pope, Rhall E.
AFFDLTR72-063.pdf