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Analytical and experimental performance of optimal controller designs for a supersonic inletThe techniques of modern optimal control theory were applied to the design of a control system for a supersonic inlet. The inlet control problem was approached as a linear stochastic optimal control problem using as the performance index the expected frequency of unstarts. The details of the formulation of the stochastic inlet control problem are presented. The computational procedures required to obtain optimal controller designs are discussed, and the analytically predicted performance of controllers designed for several different inlet conditions is tabulated. The experimental implementation of the optimal control laws is described, and the experimental results obtained in a supersonic wind tunnel are presented. The control laws were implemented with analog and digital computers. Comparisons are made between the experimental and analytically predicted performance results. Comparisons are also made between the results obtained with continuous analog computer controllers and discrete digital computer versions.
Document ID
19730010076
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Zeller, J. R. (NASA Lewis Research Center Cleveland, OH, United States)
Lehtinen, B. (NASA Lewis Research Center Cleveland, OH, United States)
Geyser, L. C. (NASA Lewis Research Center Cleveland, OH, United States)
Batterton, P. G. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-7188
E-7173
Accession Number
73N18803
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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