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Developments in optimized load calculation and extreme load detection: summary of EADS-CASA’s main static loads activities in CleanSky Smart Fixed Wing Aircraft, work package on Advanced Loads Control Techniques

  • Ignacio Ruiz JuretschkeEmail author
  • Alberto García Bosque
  • Javier Hilario Montes
  • María Calvo Blanco
Original Paper

Abstract

EADS-CASA’s Static Loads Domain participated of the Clean Sky initiative developing several activities targeting the improvement of the available static loads calculation methodologies within the work package on Advanced Loads Control Techniques of the CleanSky Smart Fixed Wing Aircraft project. This paper summarizes the progress made in the two most relevant activities, namely the optimized preliminary load calculation method, also known as aircraft response confinement method, and the extreme load detection method. The first methodology targets the calculation of design loads by means of constrained optimization performed on the loads model, and has shown to be a quick but highly conservative methodology. The second method tries to reduce the number of maneuver simulations by means of optimal case selection, and has shown to be a very powerful and efficient tool.

Keywords

Static load Extreme Optimum load Smart Fixed Wing Aircraft CleanSky 

Abbreviations

1P Loads

Propeller in-plane loads

ARC

Aircraft response confinement

CASA

Construcciones Aeronáuticas Sociedad Anónima

c.g.

Center of gravity

CoC

Center of competence

CS

Certification specification, published by the EASA

EADS

European Aeronautic Defence and Space Company

EASA

European Aviation Safety Agency

FAA

Federal Aviation Administration

FAR

Federal Aviation Regulations, published by the FAA.

FCL

Flight control laws

FCS

Flight control system

ITD

Integrated technology demonstrator

JAA

Joint Aviation Authorities

JAR

Joint Aviation Regulations, published by the JAA.

kCAS

Calibrated air speed in knots

kEAS

Equivalent air speed in knots

MS

Monitor station

MTOW

Maximum take-off weight

MZFW

Maximum zero fuel weight

NaN

Not a number

OEW

Operating empty weight

R&T

Research and technology

RMSE

Root mean square error

SDC

Structural design criteria

SFWA

Smart Fixed Wing Aircraft

α

Angle of attack

β

Angle of side slip

δ

Control surface deflection

p

Roll rate

q

Pitch rate

r

Yaw rate

\(\dot {p}\)

Roll acceleration

\(\dot {q}\)

Pitch acceleration

\(~\dot {r}\)

Yaw acceleration

\(\vec {V}\)

Loads model variable vector

\({L_i}\)

Load at monitor stations

Notes

Acknowledgements

The activities depicted herein have received funding from the European Union’s Horizon 2020 research and innovation program under grant agreement No CSJU-GAM-SFWA-2008-001.

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Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2019

Authors and Affiliations

  • Ignacio Ruiz Juretschke
    • 1
    • 2
    Email author
  • Alberto García Bosque
    • 1
  • Javier Hilario Montes
    • 1
    • 2
  • María Calvo Blanco
    • 1
  1. 1.ADS Flight Physics CoCMadridSpain
  2. 2.UC3MMadridSpain

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