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Analytical design and evaluation of an active control system for helicopter vibration reduction and gust response alleviation

Author
Miao, W.
Published
Jul 1, 1980.
Physical Description
1 electronic document
Additional Creators
Taylor, R. B., Zwicke, P. E., and Gold, P.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
An analytical study was conducted to define the basic configuration of an active control system for helicopter vibration and gust response alleviation. The study culminated in a control system design which has two separate systems: narrow band loop for vibration reduction and wider band loop for gust response alleviation. The narrow band vibration loop utilizes the standard swashplate control configuration to input controller for the vibration loop is based on adaptive optimal control theory and is designed to adapt to any flight condition including maneuvers and transients. The prime characteristics of the vibration control system is its real time capability. The gust alleviation control system studied consists of optimal sampled data feedback gains together with an optimal one-step-ahead prediction. The prediction permits the estimation of the gust disturbance which can then be used to minimize the gust effects on the helicopter.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19800019868.
Accession ID: 80N28369.
NASA-CR-152377.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15721873