Frequency versus time domain adaptive control algorithms for the active control of helicopter structural response

J. T. Pearson, R. M. Goodall

Research output: Contribution to journalConference article

4 Citations (Scopus)

Abstract

The helicopter represents a very complex system, which produces unique vibration problems. This high level of vibration experienced on the helicopter has been an unfortunate feature throughout its existence, and considerable efforts have been expended over many years to reduce vibration to levels typical of other forms of air transport. The work presented has been undertaken on a project in collaboration with Westland Helicopters Limited and aims to identify possible improvements to an existing control strategy which has already been concerned with minimising the structural vibration of a helicopter, and is achieved by measuring the vibration at a number of points on the fuselage using accelerometers. This information is processed by a multivariable control algorithm which calculates a set of control forces for a set of hydraulic actuators, located at strategic points in the structure. Vibration reductions result from the combination of the actuator control forces with those induced in the fuselage by the rotor.

Original languageEnglish
Pages (from-to)712-717
Number of pages6
JournalIEE Conference Publication
Volume2
Issue number332
Publication statusPublished - 1991
Externally publishedYes
EventInternational Conference on CONTROL '91 - Edinburgh, Scotl
Duration: 25 Mar 199128 Mar 1991

Fingerprint

Helicopters
Fuselages
Force control
Hydraulic actuators
Accelerometers
Large scale systems
Actuators
Rotors
Air

Cite this

@article{6a353e76a53a427091eea2ffaca61fd0,
title = "Frequency versus time domain adaptive control algorithms for the active control of helicopter structural response",
abstract = "The helicopter represents a very complex system, which produces unique vibration problems. This high level of vibration experienced on the helicopter has been an unfortunate feature throughout its existence, and considerable efforts have been expended over many years to reduce vibration to levels typical of other forms of air transport. The work presented has been undertaken on a project in collaboration with Westland Helicopters Limited and aims to identify possible improvements to an existing control strategy which has already been concerned with minimising the structural vibration of a helicopter, and is achieved by measuring the vibration at a number of points on the fuselage using accelerometers. This information is processed by a multivariable control algorithm which calculates a set of control forces for a set of hydraulic actuators, located at strategic points in the structure. Vibration reductions result from the combination of the actuator control forces with those induced in the fuselage by the rotor.",
author = "Pearson, {J. T.} and Goodall, {R. M.}",
year = "1991",
language = "English",
volume = "2",
pages = "712--717",
journal = "IEE Conference Publication",
issn = "0537-9989",
publisher = "Institution of Engineering and Technology",
number = "332",

}

Frequency versus time domain adaptive control algorithms for the active control of helicopter structural response. / Pearson, J. T.; Goodall, R. M.

In: IEE Conference Publication, Vol. 2, No. 332, 1991, p. 712-717.

Research output: Contribution to journalConference article

TY - JOUR

T1 - Frequency versus time domain adaptive control algorithms for the active control of helicopter structural response

AU - Pearson, J. T.

AU - Goodall, R. M.

PY - 1991

Y1 - 1991

N2 - The helicopter represents a very complex system, which produces unique vibration problems. This high level of vibration experienced on the helicopter has been an unfortunate feature throughout its existence, and considerable efforts have been expended over many years to reduce vibration to levels typical of other forms of air transport. The work presented has been undertaken on a project in collaboration with Westland Helicopters Limited and aims to identify possible improvements to an existing control strategy which has already been concerned with minimising the structural vibration of a helicopter, and is achieved by measuring the vibration at a number of points on the fuselage using accelerometers. This information is processed by a multivariable control algorithm which calculates a set of control forces for a set of hydraulic actuators, located at strategic points in the structure. Vibration reductions result from the combination of the actuator control forces with those induced in the fuselage by the rotor.

AB - The helicopter represents a very complex system, which produces unique vibration problems. This high level of vibration experienced on the helicopter has been an unfortunate feature throughout its existence, and considerable efforts have been expended over many years to reduce vibration to levels typical of other forms of air transport. The work presented has been undertaken on a project in collaboration with Westland Helicopters Limited and aims to identify possible improvements to an existing control strategy which has already been concerned with minimising the structural vibration of a helicopter, and is achieved by measuring the vibration at a number of points on the fuselage using accelerometers. This information is processed by a multivariable control algorithm which calculates a set of control forces for a set of hydraulic actuators, located at strategic points in the structure. Vibration reductions result from the combination of the actuator control forces with those induced in the fuselage by the rotor.

UR - http://www.scopus.com/inward/record.url?scp=0025791613&partnerID=8YFLogxK

M3 - Conference article

VL - 2

SP - 712

EP - 717

JO - IEE Conference Publication

JF - IEE Conference Publication

SN - 0537-9989

IS - 332

ER -