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Application of an adaptive blade control algorithm to a gust alleviation systemThe feasibility of an adaptive control system designed to alleviate helicopter gust induced vibration was analytically investigated for an articulated rotor system. This control system is based on discrete optimal control theory, and is composed of a set of measurements (oscillatory hub forces and moments), an identification system using a Kalman filter, a control system based on the minimization of the quadratic performance function, and a simulation system of the helicopter rotor. The gust models are step and sinusoidal vertical gusts. Control inputs are selected at the gust frequency, subharmonic frequency, and superharmonic frequency, and are superimposed on the basic collective and cyclic control inputs. The response to be reduced is selected to be that at the gust frequency because this is the dominant response compared with sub- and superharmonics. Numerical calculations show that the adaptive blade pitch control algorithm satisfactorily alleviates the hub gust response. Almost 100% reduction of the perturbation thrust response to a step gust and more than 50% reduction to a sinusoidal gust are achieved in the numerical simulations.
Document ID
19840002012
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Saito, S. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1983
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.15:85848
NASA-TM-85848
A-9497
Accession Number
84N10079
Funding Number(s)
PROJECT: RTOP 505-42-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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