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Study of synthesis techniques for insensitive aircraft control systemsInsensitive flight control system design criteria was defined in terms of maximizing performance (handling qualities, RMS gust response, transient response, stability margins) over a defined parameter range. Wing load alleviation for the C-5A was chosen as a design problem. The C-5A model was a 79-state, two-control structure with uncertainties assumed to exist in dynamic pressure, structural damping and frequency, and the stability derivative, M sub w. Five new techniques (mismatch estimation, uncertainty weighting, finite dimensional inverse, maximum difficulty, dual Lyapunov) were developed. Six existing techniques (additive noise, minimax, multiplant, sensitivity vector augmentation, state dependent noise, residualization) and the mismatch estimation and uncertainty weighting techniques were synthesized and evaluated on the design example. Evaluation and comparison of these six techniques indicated that the minimax and the uncertainty weighting techniques were superior to the other six, and of these two, uncertainty weighting has lower computational requirements. Techniques based on the three remaining new concepts appear promising and are recommended for further research.
Document ID
19770014950
Document Type
Contractor Report (CR)
Authors
Harvey, C. A. (Honeywell, Inc. Minneapolis, MN, United States)
Pope, R. E. (Honeywell, Inc. Minneapolis, MN, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1977
Subject Category
CYBERNETICS
Report/Patent Number
NASA-CR-2803
HONEYWELL-76-SRC/37
Funding Number(s)
CONTRACT_GRANT: NAS1-13680
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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