1. Smart Fixed-Wing Aircraft

2. SFWA-ITD overview
Le Bourget June 2013

3. SFWA-ITD overview  50% cut in CO2 emissions
Aircraft manufacturers 20-25%
Integration
Engine manufacturers 15-20%
Operations 5-10%
Air Traffic Management
Technologies are key towards ACARE targets, but can only deploy their benefits through smart integration
ACARE: Advisory Council for Aeronautics Research in Europe
Le Bourget June 2013

4. SFWA-ITD overview 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:
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
TE– SFWA technologies for a Green ATS
Output providing data to:
Le Bourget June 2013

5. SFWA-ITD ARM SFWA-ITD overview SFWA-ITD technical priorities and roadmap - Major demonstrators
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 A with modified wing
Selected in April 2009
Selection in Q3 / 2011
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
3. Innovative Engine Demonstrator Flying Testbed
Objective: Demonstrate viability of full scale innovative engine concept in operational condition
Airbus A with modified wing
Selected April 2010
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”
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
Le Bourget June 2013

6. SFWA-ITD overview SFWA 0: Selected technologies Selected Selected
Airbus /
SAAB
Technology Development
Technology Integration
Flight Demo Design
Flight Demonstration
Airbus
SFWA3:
Flight Demonstration
Dassault
SAAB
SFWA1:
Smart Wing Technology
SFWA2:
New Configuration
Selected
technologies
validated in
large scale
flight demos
at TRL > 6
Selected
Technologies
developed at
TRL 4
Selected
Technologies
integrated at
TRL 4 or 5
Technologies
enter at
TRL 2 or 3
Airbus
SFWA3.1
High Speed Smart Wing
Flight Demonstrator
Airbus
SFWA1.1
Flow Control
Airbus
SFWA2.1
Integration of Smart Wing
into OAD
SFWA3.2
Low Speed Smart Wing
Flight Demonstrator
Airbus
Dassault
SFWA1.2
Load Control
Dassault
SFWA2.2
Integration of Other Smart
Components into OAD
SFWA1.3
Integrated Flow & Load Control Systems
NL-Cluster
Airbus
SFWA3.3
Innovative Engine Demonstrator
Flying Test Bed
Airbus
SFWA2.3
Interfaces & Technology
Assessment
Airbus
SFWA3.4
Long Term Technology
Flight Demonstrator
Airbus
SFWA3.5
Innovative Empenage
Le Bourget June 2013

7. Active Flow Control: Overview Active flow control system functionality testing
Integrated Design and Evaluation of AFC system
AFC System Modeling and Simulation
AFC System Ground Testing
Future Activities
AFLoNext
CS2 ?
Key message:
Good AFC system performance demonstrated in ground tests for normal operation
Le Bourget June 2013

8. SFWA Overview Passive Buffet Control for Lam. & Turb. Wings
Progress achieved on Shock Control Bumps in 2012
CFD Studies (USTUTT)
Wind Tunnel Studies (UCAM)
Total pressure
loss in %
Le Bourget June 2013
SFWA-ITD Consortium Confidential

9. SFWA-ITD overview SFWA large demo´s with focus on Bizjets Kp x
Contribution in SFWA Large Aircraft Demo´s
SFWA large demo´s with focus on Bizjets
Smart Flaps
Innovative Rear Empenage
Natural Laminar Flow Wing Kp x
Structures and systems integration for innovative Wing
Krueger Flaps for laminar wing
Leading Edge Coating
High Aspect Ratio
Load and vibration alleviation
Le Bourget June 2013

10. Control of loads and vibrations Simulations and demonstration strategy
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
Le Bourget June 2013

11. High Speed Demonstrator Passive
Le Bourget June 2013

12. Laminar Wing aerodynamic layout and performance
SFWA-ITD overview
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
Port wing
Laminar wing structure concept option 2
Starboard wing
Laminar wing structure concept option 1
Laminar Wing aerodynamic layout and performance
Laminar Wing Ground test
demonstrator to address structural, system and manufacturing aspects
Le Bourget June 2013

13. BLADE Partnership (Wing Perimeter)
SFWA-ITD overview
BLADE Partnership (Wing Perimeter)
Le Bourget June 2013

14. Smart Wing flight test instrumentation
Status March 2013 (ARM)
expected laminar flow A
Representation of laminar
Wing on A340 flying test bed A
Extend of laminar flow
Smart Wing observation camera view angle from potential observer pod position (Airbus) B E D F
Flush mount hot film sensor for the detection of flow separation (ONERA)
Infrared Image of laminar –turbulent flow transition on wing surface (ONERA)
In-Flight Monitoring of Wing Surface with Quasi tangential Reflectometry and Shadow Casting “WING REFLECTOMETRY” (FTI) C
Phase locked PIV for quantitive wake-flow diagnostics of CROR-blades in flight (Illustration: DLR, 2009)
Le Bouget June 2013

15. Working Principles The system consists in: Processing
An illumination source:
high power pulse laser to generate a light sheet
A 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
Le Bourget June 2013

16. Smart Wing manufacturing and assembly scenarios
Le Bourget June 2013

17. CROR demonstration engine Flying Test Bed
Le Bourget June 2013

18. CROR engine integration concepts
RR/ SN/ AI
Decission Sept 2011:
Engine concept for integration studies
Engine concept for integration studies
Demo Engine for Flight Test
Le Bourget June 2013

19. Thank you for your attention