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Smart Fixed-Wing Aircraft

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Presentation on theme: "Smart Fixed-Wing Aircraft"— Presentation transcript:

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

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