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Helicopter load alleviation using active control

Published online by Cambridge University Press:  03 February 2016

M. Voskuijl ,
D. J. Walker  and
B. J. Manimala
M. Voskuijl
Affiliation:
Department of Engineering, The University of Liverpool, Liverpool, UK
D. J. Walker
Affiliation:
Department of Engineering, The University of Liverpool, Liverpool, UK
B. J. Manimala
Affiliation:
Department of Engineering, The University of Liverpool, Liverpool, UK
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Abstract

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This paper discusses how structural load objectives can be included in a rotorcraft flight control system design in an efficient and straightforward way using multivariable control techniques. Several research studies have indicated that pitch link loads for various rotorcraft types can reach high or even unacceptable values, both in steady state and maneuvering flight. This is especially the case for high-speed aggressive maneouvers. Pitch link loads at high-speed flight are therefore taken as a case study. A novel longitudinal control system is presented, designed to reduce helicopter pitch-link loads during high-speed longitudinal manoeuvres whilst providing a pitch attitude command attitude hold response type. The design is based on a high-order model of a helicopter representative of the UH-60 Black Hawk. New metrics are presented for the analysis of structural loads that can be used in combination with ADS-33 handling qualities requirements.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1137 , November 2008 , pp. 663 - 672
Copyright
Copyright © Royal Aeronautical Society 2008

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