Le Bourget June 2013 SFWAITD overview Aircraft manufacturers 2025 Engine manufacturers 1520 Operations 510 Air Traffic Management 50 cut in CO2 emissions ACARE Advisory Council for Aeronautics Research in Europe ID: 260443
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Slide1
Smart Fixed-Wing AircraftSlide2
Le Bourget June 2013
SFWA-ITD overviewSlide3
Aircraft manufacturers 20-25%
Engine manufacturers 15-20%
Operations 5-10%
Air Traffic Management
50% cut in CO2 emissions
ACARE: Advisory Council for Aeronautics Research in Europe
Technologies are key towards ACARE targets, but can only deploy their benefits through smart integration
Integration
Le Bourget June 2013
SFWA-ITD
overviewSlide4
Innovative Powerplant Integration
Technology Integration
Large Scale Flight Demonstration Impact of airframe flow field on Propeller design (acoustic, aerodynamic, vibration)
Impact of open rotor configuration on airframe (Certification capabilities, structure, vibrations...)
Innovative empennage design
Smart Wing Technologies
Technology Development
Technology Integration
Large Scale Flight Demonstration
Natural Laminar Flow (NLF)
Hybrid Laminar Flow (HLF)
Active and passive load control
Novel enabling materials
Innovative manufacturing scheme
SAGE ITD –
CROR engine
SGO –
Systems for Green Operation
Input
connecting
to
:
TE–
SFWA technologies for a Green ATS
Output
providing
data
to
:
Le Bourget June 2013
SFWA-ITD overviewSlide5
Le Bourget June 2013
1. High Speed Flight Demonstrator
Objective:
Large scale flight test of passive and active flow and loads control solutions on all new innovative wing concepts to validate low drag solutions at representative Mach and Reynolds Numbers. Envisaged to be used at least in two major phases of the project.
Airbus A340-300 with modified wing
4. Long Term Technology Flight Demonstrator
Objective:
Validation of durability and robustness of Smart Wing technologies in operational environment
In Service Transport Aircraft
Airbus A300 “Beluga”
3. Innovative Engine Demonstrator Flying
Testbed
Objective:
Demonstrate viability of full scale innovative engine concept in operational condition
Airbus A340-500 with modified wing
2. Low Speed Demonstrator
Objective:
Validation flight testing of High Lift solution to support / enable the innovative wing / low drag concepts with a full scale demonstrator.
2.1 Smart Flap large scale ground demo
/
DA Falcon type Bizjet trailing edge
2.2 Low Speed Vibration Control Flight Test Demonstration
DA Falcon F7X
Selected in April 2009
Selection in Q3 / 2011
Selected April 2010
Selection(s) part of
technology roadmap
5. Innovative
Empenage
Ground Demonstrator
Objective:
Validation of a structural rear
empenage
concept for noise shielding engine integration on business jets
SFWA design
Selected Q4 2011
SFWA-ITD ARM 2013 - SFWA-ITD overview
SFWA-ITD technical priorities and roadmap - Major demonstratorsSlide6
Flight Demo Design
Technology Integration
Technology Development
SFWA3.5
Innovative Empenage
Airbus
SFWA1:
Smart Wing Technology
SFWA2:
New Configuration
SFWA3:
Flight Demonstration
SFWA 0:
SFWA1.2
Load Control
SFWA1.1
Flow Control
SFWA1.3
Integrated Flow & Load Control Systems
NL-Cluster
Airbus
Airbus
Dassault
Airbus /
SAAB
SAAB
Airbus
SFWA2.1
Integration of Smart Wing
into OAD
Airbus
SFWA2.2
Integration of Other Smart
Components into OAD
Dassault
SFWA2.3
Interfaces & Technology
Assessment
Airbus
SFWA3.1
High Speed Smart Wing
Flight Demonstrator
Airbus
SFWA3.3
Innovative Engine Demonstrator
Flying Test Bed
Airbus
SFWA3.2
Low Speed Smart Wing
Flight Demonstrator
Dassault
SFWA3.4
Long Term Technology
Flight Demonstrator
Airbus
Flight Demonstration
Technologies
enter at
TRL 2 or 3
Selected
Technologies
developed at
TRL 4
Selected
Technologies
integrated at
TRL 4 or 5
Selected
technologies
validated in
large scale
flight demos
at TRL > 6
Le Bourget June 2013
SFWA-ITD overviewSlide7
Active Flow Control: Overview
Active flow control system functionality testing
Key message:
Good AFC system performance demonstrated in ground tests for normal operation
AFLoNext
CS2 ?
Le Bourget June 2013Slide8
Progress achieved on
Shock Control Bumps in 2012
SFWA-ITD Consortium Confidential
Wind Tunnel Studies (UCAM)
CFD Studies (USTUTT)
Total pressure
loss in %
SFWA Overview
Passive Buffet Control for Lam. &
Turb
. Wings
Le Bourget June 2013Slide9
Le Bourget June 2013
Natural Laminar Flow Wing
Kp
x
Leading Edge Coating
Structures and systems integration for innovative Wing
High Aspect Ratio
Krueger Flaps for laminar wing
Load and vibration alleviation
Smart Flaps
Innovative Rear Empenage
SFWA-ITD overview
Contribution in SFWA Large Aircraft Demo´s
SFWA large demo´s with focus on BizjetsSlide10
Le Bourget June 2013
Validation plan in 2 steps
Phase 1: Ground Tests
Validation of control law design
methodology
Validation of ability to control
vibrations due to a well known
excitation force
Phase 2: Flight Tests
Validation of vibration reduction
function in real environment
Control of loads and vibrations Simulations and demonstration strategySlide11
Le Bourget June 2013
High
Speed Demonstrator PassiveSlide12
Laminar Wing Ground test
demonstrator to address structural, system and manufacturing aspects
Port wing
Laminar wing structure concept option 2
Starboard wing
Laminar wing structure concept option 1
Laminar Wing aerodynamic layout and performance
Smart Passive Laminar Flow Wing
Design of an all new natural laminar wing
Proof of natural laminar wing concept in wind tunnel tests
Use of novel materials and structural concepts
Exploitation of structural and system integration together with tight tolerance / high quality manufacturing methods in a large scale ground test demonstrator
Large scale flight test demonstration of the laminar wing in operational conditions
Le Bourget June 2013
SFWA-ITD overviewSlide13
Le Bourget June 2013
13
SFWA-ITD overview
BLADE Partnership (Wing Perimeter)Slide14
Smart Wing observation camera view angle from potential observer pod position (Airbus)
Infrared Image of laminar –turbulent flow transition on wing surface (ONERA)
Flush mount hot film sensor for the detection of flow separation (ONERA)
expected laminar flow
A340-300
Representation of laminar
Wing on A340 flying test bed
Extend of laminar flow
A
B
D
E
Le Bouget June 2013
14
Smart
Wing flight test instrumentation
Phase locked PIV for quantitive wake-flow diagnostics of CROR-blades
in flight
(Illustration: DLR, 2009)
Status March 2013 (ARM)
In-Flight Monitoring of Wing Surface with Quasi tangential Reflectometry and Shadow Casting “WING REFLECTOMETRY” (FTI)
F
CSlide15
The system consists in:
An illumination source:
high power pulse laser to generate a light sheetA seeding system:
using particles contained in the atmosphere (natural) or spraying particles
An optical part
:
2 or more high speed / high resolution cameras, set perpendicularly to the laser sheet to capture the illuminated particles, by cross-correlation
Post-processing and correlation tools
Processing
Two pictures are taken in a timeframe of 0,1µs: the illuminated particles are captured at t and (t + ∆t).
As the particles move, the displacement is measured and the velocity vector is computed
Example of a velocity field measured with the PIV technique
Working Principles
Le Bourget June 2013Slide16
Le Bourget June 2013
16
Smart
Wing manufacturing and assembly scenariosSlide17
Le Bourget June 2013
17
CROR
demonstration engine Flying Test Bed Slide18
Le Bourget June 2013
CROR
engine integration concepts
Demo Engine for Flight Test
Engine concept for integration studies
Engine concept for integration studies
RR/ SN/ AI
Decission Sept 2011:Slide19
Thank you for your attention