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An optimal control approach for alleviation of 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 in aeroplane and helicopter operation modes obtained by an optimal control methodology based on the actuation of elevators, wing flaperons and swashplate is examined. An optimal observer for state estimate is included in the compensator synthesis, with the Kalman-Bucy filter applied in the presence of stochastic noise. Tiltrotor dynamics is simulated through an aeroelastic model that couples rigid-body motion with wing and proprotor structural dynamics. An extensive numerical investigation examines effectiveness and robustness of the applied control procedure, taking into account the action of both deterministic and stochastic vertical gusts. In addition, a passive pilot model is included in the aeroelastic loop and the corresponding effects on uncontrolled and controlled gust response are analysed.

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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