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An optimal control approach for alleviationof tiltrotor gust response

Published online by Cambridge University Press:  27 January 2016

D. Muro ,
M. Molica Colella ,
J. Serafini  and
M. Gennaretti
D. Muro
Affiliation:
University Roma Tre, Department of Mechanical and Industrial Engineering, Via della Vasca Navale, Rome, Italy
M. Molica Colella
Affiliation:
University Roma Tre, Department of Mechanical and Industrial Engineering, Via della Vasca Navale, Rome, Italy
J. Serafini
Affiliation:
University Roma Tre, Department of Mechanical and Industrial Engineering, Via della Vasca Navale, Rome, Italy
M. Gennaretti*
Affiliation:
University Roma Tre, Department of Mechanical and Industrial Engineering, Via della Vasca Navale, Rome, Italy
*
m.gennaretti@uniroma3.it
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Abstract

The alleviation of gusts effects on a tiltrotor inaeroplane and helicopter operation modes obtained byan optimal control methodology based on theactuation of elevators, wing flaperons andswashplate is examined. An optimal observer forstate estimate is included in the compensatorsynthesis, with the Kalman-Bucy filter applied inthe presence of stochastic noise. Tiltrotor dynamicsis simulated through an aeroelastic model thatcouples rigid-body motion with wing and proprotorstructural dynamics. An extensive numericalinvestigation examines effectiveness and robustnessof the applied control procedure, taking intoaccount the action of both deterministic andstochastic vertical gusts. In addition, a passivepilot model is included in the aeroelastic loop andthe corresponding effects on uncontrolled andcontrolled gust response are analysed.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1180 , June 2012 , pp. 651 - 666
Copyright
Copyright © Royal Aeronautical Society 2012 

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