Towards an advanced nonlinear rotorcraft flight control systemdesign
Njaka, C.E.
Menon, P.K.
Cheng, V.H.L.
NASA Ames Res. Center, Moffett Field, CA;
This paper appears in: Digital Avionics Systems Conference, 1994. 13th DASC., AIAA/IEEE
Publication Date: 30 Oct-3 Nov 1994
On page(s): 190-197
Meeting Date: 10/30/1994 - 11/03/1994
Location: Phoenix, AZ, USA
ISBN: 0-7803-2425-0
References Cited: 15
INSPEC Accession Number: 4852696
Digital Object Identifier: 10.1109/DASC.1994.369483
Current Version Published: 2002-08-06
Abstract
Traditional rotorcraft flight control designs rely heavily on
plant models which have been linearized about various operating set
points. These designs are only valid for operating conditions close to
the original trim points and suffer performance degradations for
significant deviations. Consequently, several linear controllers are
designed and scheduled to cover the operational flight envelope. An
alternate approach that uses the inherent nonlinearities of the plant
model may provide improved performance. Described herein are the initial
results of a rotorcraft control design methodology that uses an
aircraft-model-based transformation to convert the input-output map of
the original nonlinear plant into a linear time-invariant system. The
validity of the design technique for attitude stabilization is evaluated
in a high-fidelity computer simulation of the UH-60 Black Hawk
helicopter
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