Transcript Document

Smart Fixed-Wing Aircraft
SFWA-ITD overview
Le Bourget June 2013
SFWA-ITD overview
 50% cut in CO2 emissions
Aircraft manufacturers 20-25%
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
SFWA-ITD overview
Input connecting to:
SAGE ITD – CROR engine
SGO –
Smart Wing Technologies
Technology Development
Technology Integration
Systems for Green
Operation
 Large Scale Flight Demonstration
 Natural Laminar Flow (NLF)
 Hybrid Laminar Flow (HLF)
 Active and passive load control
Innovative Powerplant Integration
 Novel enabling materials
 Technology Integration
 Innovative manufacturing scheme
 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
Output providing data to:
TE– SFWA technologies for a
Green ATS
Le Bourget June 2013
SFWA-ITD ARM 2013 - 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 A340-300 with modified wing
Selected in April 2009
2. Low Speed Demonstrator
Selection in Q3 / 2011
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
Selected April
Airbus A340-500 with modified wing
2010
4. Long Term Technology Flight Demonstrator
Objective: Validation of durability and robustness of Smart Wing technologies in operational
environment
Selection(s) part of
In Service Transport Aircraft
technology roadmap
Airbus A300 “Beluga”
5. Innovative Empenage Ground Demonstrator
Objective: Validation of a structural rear empenage concept for noise shielding engine
integration on business jets
Selected Q4
SFWA design
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2011
SFWA-ITD overview
SFWA 0:
Airbus /
SAAB
Airbus
Dassault
SFWA1:
Smart Wing Technology
SFWA1.1 Airbus
Flow Control
Selected
Technologies
Airbus
SFWA1.2
Technologies
enter at Load
Control
developed at
TRL 2 or 3
NL-Cluster TRL 4
SFWA1.3
Integrated Flow & Load
Control Systems
SAAB
SFWA2:
New Configuration
Airbus
SFWA2.1
Integration of Smart Wing
into OAD
Selected
Technologies
at
SFWA2.2
Integration of Other Smart TRL 4 or 5
Dassault
integrated
Components into OAD
Airbus
SFWA2.3
Interfaces & Technology
Assessment
Technology Development
Technology Integration
SFWA3:
Flight Demonstration
Airbus
SFWA3.1
High Speed Smart Wing
Flight Demonstrator
Selected
technologies
SFWA3.2
Dassault
Low Speed Smart Wing
validated in
Flight Demonstrator
large scale
flight
demos
Airbus
SFWA3.3
at TRL > 6
Innovative Engine Demonstrator
Flying Test Bed
SFWA3.4
Long Term Technology
Flight Demonstrator
SFWA3.5
Innovative Empenage
Airbus
Airbus
Flight Demo Design
Flight Demonstration
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Active Flow Control: Overview
Active flow control system functionality testing
Future
Activities
AFC System
Ground Testing
AFLoNext
CS2 ?
AFC System
Modeling and
Simulation
Integrated
Design and
Evaluation of
AFC system
Key message:
Good AFC system performance demonstrated in ground tests for normal operation
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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 %
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SFWA-ITD Consortium Confidential
SFWA-ITD overview
SFWA large
demo´s with focus
on Bizjets
Smart Flaps
Innovative Rear
Empenage
Natural Laminar Flow
Wing
Kp
Structures and systems
integration for innovative
Wing
x
Krueger Flaps for laminar
wing
Leading Edge Coating
High Aspect Ratio
Load and vibration
alleviation
2009/261 19.37.24
Outils_CS
Analyse turbulence V289
VENTZ (M/S) P-F
REAL PART
8
Contribution in
SFWA Large
Aircraft Demo´s
6
4
2
0
30
32
34
36
38
40
42
44
46
48
50
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-4
-6
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TIME (S)
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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
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High Speed Demonstrator Passive
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SFWA-ITD overview
Smart Passive Laminar Flow Wing
Laminar Wing Ground test
demonstrator to address
structural, system and
manufacturing aspects
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Design of an all new natural laminar wing

Large scale flight test demonstration of the laminar
wing in operational conditions
Proof of natural laminar wing concept in wind tunnel tests
Use of novel materials and structural concepts
Starboard wing
Laminar wing structure
concept option 1
Exploitation of structural and system integration together
with tight tolerance / high quality manufacturing methods
in a large scale ground test demonstrator
Port wing
Laminar wing structure
concept option 2
Laminar Wing aerodynamic
layout and performance
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SFWA-ITD overview
BLADE Partnership (Wing Perimeter)
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Smart Wing flight test instrumentation
Status March 2013 (ARM)
A
Extend of
laminar flow
A340-300
Smart Wing observation camera view angle from
potential observer pod position (Airbus)
Representation of laminar
Wing on A340 flying test bed
E
D
C
Phase locked PIV for quantitive wakeflow diagnostics of CROR-blades in
flight (Illustration: DLR, 2009)
Infrared Image of laminar –
turbulent flow transition
on wing surface (ONERA)
Flush mount hot film
sensor for the detection
of flow separation
(ONERA)
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B
F
In-Flight Monitoring of Wing
Surface with Quasi tangential
Reflectometry and Shadow
Casting “WING REFLECTOMETRY”
(FTI)
14
Working Principles
The system consists in:
 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
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Smart Wing manufacturing and assembly scenarios
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CROR demonstration engine Flying Test Bed
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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
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Thank you for your attention