Download - Smart Fixed-Wing Aircraft
Smart Fixed-Wing Aircraft
Le Bourget June 2013
SFWA-ITD overview
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 overview
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 TechnologiesTechnology DevelopmentTechnology 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 overview
Le Bourget June 2013
1. High Speed Flight DemonstratorObjective: 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 DemonstratorObjective: Validation of durability and robustness of Smart Wing technologies in operational
environment In Service Transport AircraftAirbus A300 “Beluga”
3. Innovative Engine Demonstrator Flying TestbedObjective: Demonstrate viability of full scale innovative engine concept in operational
condition Airbus A340-500 with modified wing
2. Low Speed DemonstratorObjective: 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 DemonstratorObjective: 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 overviewSFWA-ITD technical priorities and roadmap - Major demonstrators
Flight Demo DesignTechnology IntegrationTechnology Development
SFWA3.5Innovative Empenage
Airbus
SFWA1: Smart Wing Technology
SFWA2: New Configuration
SFWA3: Flight Demonstration
SFWA 0:
SFWA1.2Load Control
SFWA1.1Flow Control
SFWA1.3Integrated Flow & Load
Control Systems
NL-Cluster
Airbus
Airbus
Dassault
Airbus /SAAB
SAABAirbus
SFWA2.1Integration of Smart Wing
into OAD
Airbus
SFWA2.2Integration of Other Smart
Components into OAD
Dassault
SFWA2.3Interfaces & Technology
Assessment
Airbus
SFWA3.1High Speed Smart Wing
Flight Demonstrator
Airbus
SFWA3.3Innovative Engine Demonstrator
Flying Test Bed
Airbus
SFWA3.2Low Speed Smart Wing
Flight DemonstratorDassault
SFWA3.4Long Term Technology
Flight Demonstrator
Airbus
Flight Demonstration
Technologies enter at
TRL 2 or 3
SelectedTechnologies developed at
TRL 4
SelectedTechnologies integrated at
TRL 4 or 5
Selectedtechnologies validated in large scale
flight demos at TRL > 6
Le Bourget June 2013
SFWA-ITD overview
Active Flow Control: OverviewActive flow control system functionality testing
Integrated Design and Evaluation of AFC system
AFC System Modeling and Simulation
AFC System Ground Testing
Future Activities
Key message: Good AFC system performance demonstrated in ground tests for normal operation
AFLoNextCS2 ?
Le Bourget June 2013
Progress achieved on Shock Control Bumps in 2012
SFWA-ITD Consortium Confidential
Wind Tunnel Studies (UCAM)CFD Studies (USTUTT)
Total pressure loss in %
SFWA OverviewPassive Buffet Control for Lam. & Turb. Wings
Le Bourget June 2013
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
Analyse turbulence V289VENTZ (M/S) P-FREAL PART
-12
-10
-8
-6
-4
-2
0
2
4
6
8
30 32 34 36 38 40 42 44 46 48 50
TIME (S)
2009/261 19.37.24Outils_CS
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
Bizjets
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 knownexcitation force
Phase 2: Flight Tests– Validation of vibration reduction
function in real environment
Control of loads and vibrations Simulations and demonstration strategy
Le Bourget June 2013
High Speed Demonstrator Passive
Laminar Wing Ground testdemonstrator 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 overview
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SFWA-ITD overview BLADE Partnership (Wing Perimeter)
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 201314
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
C
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
Working Principles
Le Bourget June 2013
Le Bourget June 201316
Smart Wing manufacturing and assembly scenarios
Le Bourget June 201317
CROR demonstration engine Flying Test Bed
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:
Thank you for your attention