5-CleanSky SFWA forum-aeArchitecture defined and integrated to DMU o 2 IR cameras (1 per wing) o Gi idGermanium windows o Calibration Plates (Black bodies) o Motorization for pitch

Month 20XX Use Tab 'Insert - Header & Footer' for Presentation Title - Siglum - Reference

Gareth Williams

Progress and achievements inachievements in CleanSky SFWALarge scale ground and flight test demonstrator R&T to develop technologies for future large transporttechnologies for future large transport aircraft

From CleanSky1 to CleanSky2


CS1 Smart Fixed Wing Aircraft -ITD (SFWA) Is a unique environment for high TRL integrated Research and Development

Provides the frame for well aligned objective driven R&T coveringProvides the frame for well aligned objective driven R&T coveringdevelopment and maturation through numerical simulation,rig demonstrators, wind tunnel testing, large scale andflight testing underconditions relevantfor operation TRL6

TRL5

TRL4 SFWA k t h l iTRL4 SFWA key technologies o NLF – wing for large transport aircraft and

bizjetso CROR engine integrationo Innovative empennage for next generation

bizjetso Innovative control surfaces

TRL3

CS2 Large Passenger Aircraft IADP (LPA)

o Innovative control surfaceso Buffet Control Technologieso Advanced load control architectures and

functiono Advanced Flight Test instrumentation

CS2 Large Passenger Aircraft IADP (LPA) Will provide a platform for even more focussed large scale, highly

integrated demonstrators with core partners and partners

Build on down best candidate technologies emerging from CleanSky 1 other national and EU R&T programs and2 3 4 5 6

Contribute to TRL - Scale

1

© AIRBUS Operations GmbH. All rights reserved. Confidential and proprietary document.

CleanSky 1 other national and EU R&T programs andadditional technologies developed in CS2 ITDs

2 3 4 5 61

SFWA NLF wing - Preparation of BLADE flight tests





AStatus April 2014

Preparation of BLADE NLF wing flight test instrumentation

A340 300 Extend of

S t Wi b ti i l f

A340-300 Extend of laminar flow

Smart Wing observation camera view angle from new observer pod position on top of fin(Airbus)Representation of laminar

Wing on A340 flying test bedB

DC

D

E

Infrared Image of laminar –turbulent flow transition on wing

f (ONERA)

Flush mount hot film sensor for the detection

f fl ti (DLR)

In-Flight Monitoring of Wing Surface with Reflectometryand Shadow Casting “WING

E

In-Flight Internal waviness measurement with

F


surface (ONERA) of flow separation (DLR) and Shadow Casting WING REFLECTOMETRY” (FTI) potentiometer arrays



Integration of IR diagnostics to BLADE Fuselage POD killed for Fin Tip Fairing

Preparation of BLADE NLF wing flight test instrumentation

Fuselage POD killed for Fin Tip Fairing Architecture defined and integrated to DMU

o 2 IR cameras (1 per wing)G i i do Germanium windows

o Calibration Plates (Black bodies)o Motorization for pitch & yaw adjustments

Do Damperso Camera heaters and dry air from cabin




Plan for 6 months, 150h of flight testing to cover Opening of the flight test domain

Objectives of the BLADE flight tests

Opening of the flight test domain Testing of the NLF wing

o Laminarity boundaries (CL, Ma) identification in reference conditionI t d ti f d fi d t b ti t th b t f l i ito Introduction of defined perturbations to assess the robustness of laminarity Validation of quality criteria (steps, gaps, waviness, routhness) Assessment of impact of athomspheric perturbations Assessment of impact of operational constraints Validation of capabilities and accuracy of CFD and WTT

Leading edge shielding testingo Assessment of Krueger flaps shieldingg p g




BLADE wing design highlights




BLADE wing design highlights




Assembly of the BLADE components to the test aircraft




Pre-testing of the BLADE IR diagnostic arrangement




BLADE demonstrator roadmap


SFWA NLF-wing ground based demonstrator (Airbus)


Advanced NLF wing leading edge concept

NLF Leading edge baseline NLF leading edge with g gstructure & system

g gadvanced structure & system


SFWA NLF- wing ground based demonstrator (GKN / Airbus)


Innovative NLF wing manufacturing technologies

Baseline leading edge skin panel

CFRP panel with co-cured stiffeners and Panel in tooling with sample aluminium rib in place.


rib attachments

SFWA NLF- wing ground based demonstrator (GKN / Airbus)


Innovative NLF wing components

Additive layer manufacturing• titanium ‘one-piece’ replaces two baseline Krueger ribsp p g• improved datums for mechanism• lightweight• no loads transferred into LE skin


SFWA NLF-wing ground based demonstrator (Airbus)


Innovative Krueger integration

P-KinematicsElectric Drives generating the

Plug-in-Actuator-Lever

P Kinematics generating the input torque

(Test-Specimen)

A340 Slat GRADrive StrutDrive-Strut (Test-Specimen)


SFWA Integration of advanced engine concepts


CROR propulsion system integration R&T

• Best disruptive powerplant candidate• Maturity too low

SFWA- CROR Aircraft Concept Top Level Aircraft RequirementsRequirementsCommercial passenger transport Aircraft Short Range130-200 PAX seat capacity

Need to understand risks & opportunities before implementation on Aircraft

p yMaximise aircraft availability & Reduce operation

costs for Airlines


Need to understand risks & opportunities before implementation on Aircraft



Progress in i l

CROR propulsion system integration R&T

numerical simulations

High Fidelity Wind Tunnel T ti

Scale 1/7Scale 1/7Scale 1/5 HSTesting

A l i dAnalysis and design

Installed propeller efficiency 88% at M=0.75

Focus is to obtain High Quality Data

Aircraft Handling Quality

Noise (EM&AI blades, high scale, installation effects)


Focus is to obtain High Quality Data



High Speed Low Speed

CROR aeroacoustic characterization

SFWA WP222 (2013)

• Unsteady blade pressure (80/rotor) /

SFWA WP224(2013)

• Far field acousticdeformation (SPA method - ON)

• Unsteady rotor loads• Near field noise

Propeller mapping incidence Mach

• Unsteady rotor loads• Some unsteady blade pressures• Installation effects /left /right /pylon/blowing

• Propeller mapping, incidence, Mach

High Fidelity Aero-acoustic database

• Propeller blade design effect (AI/SN/RR)• Near field noise


High Fidelity Aero acoustic database



C O

Isolated Full aircraftPylon only

CROR low speed aeroacoustic characterization

Noise Carpet of 5 first harmonics of Blade Passing Frequency of the Front Rotor

5dB

Experimentally obtained noise signatures of isolated and installed CROR indicate that future noise regulations can be met


CROR indicate that future noise regulations can be met



f C O &

• Strong interest to continue effort:

Next challenges for CROR propulsion system integration R&T

o Complete Aircrafto Comparison to experiments /calibrations

Further develop methods (bl d d f ti / bl do Further develop methods (blade deformation / blade transition / boundary layer refraction…)

K t E i i bilit d t ti• Key to Economic viability demonstrations:• Reduced fuselage clearance, diameter trades,

alternate configuration, design refinements…g , g

• Additional R&T targeted in CleanSky 2

Numerical simulations ongoing to prepare R&T activities in CleanSky 2




Preliminary Architecture on CROR FTDPreparation of Flight Test instrumentation for CROR demo engine flight tests

Configuration: Laser pointing upwards, cameras installed in cabin

Example of geometry adjustment without major architectural change

Example of A/C window f i li d

Phase-locked PIV for quantitive wake-flow di ti f CROR for inclined

camera installation

diagnostics of CROR-blades in flight (Illustration: DLR



© Airbus Operations GmbH. All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of Airbus Operations GmbH. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of Airbus Operations GmbH. This document and its content shall not be used for any purpose other than that for which it is supplied. The statements made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supporting grounds for these statements are not shown, Airbus Operations GmbH will be pleased to explain the basis thereof. AIRBUS, its logo, A300, A310, A318, A319, A320, A321, A330, A340, A350, A380, A400M are registered trademarks.

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5-CleanSky SFWA forum-aeArchitecture defined and integrated to DMU o 2 IR cameras (1 per wing) o Gi idGermanium windows o Calibration Plates (Black bodies) o Motorization for pitch