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Influence of H 2 and \( {{\mathcal{L}}}_{\infty } \) Criteria on Feed-Forward Gust Loads Control Optimized for the Minimization of Wing Box Structural Mass on an Aircraft with Active Winglets

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Smart Intelligent Aircraft Structures (SARISTU)

Abstract

This chapter presents the estimation of potential wing box mass saving enabled by means of active loads alleviation on a regional aircraft equipped with winglet control surfaces. As for the investigated aircraft, the inner wing is sized by maneuvers, and the minimization of structural weight of the wing box by active gust loads alleviation primarily affects the outer wing. Vice versa the minimization of structural weight of the inner wing can mainly be achieved by maneuver loads alleviation. The presented loads alleviation optimization directly minimizes the wing box mass required to sustain maneuver and gust loads. It is shown that the choice of the cost function has a significant influence on this optimum and the resulting wing box mass. Both H 2 and \( {\mathbf{\mathcal{L}}}_{\infty } \) criteria are investigated. Based on the optimization results, a potential total wing box mass saving is proposed for further aircraft performance assessment.

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Abbreviations

A/C:

Aircraft

AIL:

Ailerons

CG:

Center of gravity

\( \vec{d}\left( t \right) \) :

Disturbance response vector

dm :

Mass of one wing segment

\( \vec{e}\left( t \right) \) :

Vector of error signals

ELE:

Elevators

\( \varvec{G}_{c} \left( s \right) \) :

Matrix of transfer functions of the SCP

GLAS:

Gust load alleviation system

\( \vec{H}\left( s \right) \) :

Vector of feed-forward controllers

h :

Height of wing segment

i :

Wing segment number

J :

Cost function

k e :

Empirical compensation factor

L :

Number of simulated samples

l :

Total number of wing segments

Length:

Span of one wing segment

M b :

Wing bending moment

m :

Wing box mass

N :

Filter length

n :

Discrete time step

s :

Laplace variable

SCP:

Secondary control path

t eq :

Equivalent skin thickness

t sp :

Spar thickness

T s :

Sampling time

\( \vec{u}_{\text{GLAS}} \left( t \right) \) :

Vector of controller commands

w(t, x, y, z):

Exogenous disturbance

w :

Chord of wing box segment

z :

Z-transform variable

MLA:

Maneuver load alleviation

MLDW:

Maximum landing weight

MTOW:

Maximum takeoff weight

VA:

Design maneuvering speed

VC:

Design cruising speed

VD:

Design dive speed

WATE:

Wingtip active trailing edge

(x 0, y 0, z 0):

Reference point at cockpit location

ρ :

Mass density

σ max :

Allowable stress at limit load

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Acknowledgments

The research leading to these results has gratefully received funding from the European Union Seventh Framework Programme (FP7/2007 2013) under Grant Agreement no 284562. Many thanks also go to all SARISTU partners for their invaluable contributions.

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Authors and Affiliations

  1. Airbus Group Innovations, Munich, 81663, Germany

    Andreas Wildschek

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  1. Andreas Wildschek
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Correspondence to Andreas Wildschek .

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Editors and Affiliations

  1. AIRBUS Operations GmbH, Bremen, Germany

    Piet Christof Wölcken

  2. EASN Technology Innovation Services, Budingen, Belgium

    Michael Papadopoulos

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Wildschek, A. (2016). Influence of H 2 and \( {{\mathcal{L}}}_{\infty } \) Criteria on Feed-Forward Gust Loads Control Optimized for the Minimization of Wing Box Structural Mass on an Aircraft with Active Winglets. In: Wölcken, P., Papadopoulos, M. (eds) Smart Intelligent Aircraft Structures (SARISTU). Springer, Cham. https://doi.org/10.1007/978-3-319-22413-8_16

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  • DOI: https://doi.org/10.1007/978-3-319-22413-8_16

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  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-22412-1

  • Online ISBN: 978-3-319-22413-8

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