Smart FixedWing Aircraft SFWAITD overview Le Bourget June

Smart Fixed-Wing Aircraft

SFWA-ITD overview Le Bourget June 2013

SFWA-ITD overview 50% cut in CO 2 emissions Aircraft manufacturers 20 -25% n atio r g e t In Engine manufacturers 15 -20% 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 Operations 5 -10% Air Traffic Management

SFWA-ITD overview Input connecting to: SAGE ITD – CROR engine SGO – Systems for Green Operation Smart Wing Technologies ØTechnology Development ØTechnology Integration Ø Large Scale Flight Demonstration Ø Natural Laminar Flow (NLF) Ø Hybrid Laminar Flow (HLF) Ø Active and passive load control Innovative Powerplant Integration Ø Novel enabling materials Ø Technology Integration Ø Innovative manufacturing scheme Ø Large Scale Flight Demonstration Ø Impact of airframe flow field on Propeller design (acoustic, aerodynamic, vibration) Ø Impact of open rotor configuration on airframe (Certification capabilities, structure, vibrations. . . ) Ø 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 A 340 -300 with modified wing Selected in April 2009 2. Low Speed Demonstrator Selection in Q 3 / 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 F 7 X 3. Innovative Engine Demonstrator Flying Testbed Objective: Demonstrate viability of full scale innovative engine concept in operational condition Selected April Airbus A 340 -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 A 300 “Beluga” 5. Innovative Empenage Ground Demonstrator Objective: Validation of a structural rear empenage concept for noise shielding engine integration on business jets Selected Q 4 SFWA design Le Bourget June 2013 2011

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

Active Flow Control: Overview Active flow control system functionality testing Future Activities AFC System Ground Testing AFLo. Next CS 2 ? 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 Le Bourget June 2013

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

SFWA-ITD overview Smart Flaps SFWA large demo´s with focus on Bizjets 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 Contribution in SFWA Large Aircraft Demo´s Le Bourget June 2013

Control of loads and vibrations Simulations and demonstration strategy Validation plan in 2 steps v Phase 1: Ground Tests – Validation of control law design methodology – Validation of ability to control vibrations due to a well known excitation force v Phase 2: Flight Tests – Validation of vibration reduction function in real environment Le Bourget June 2013

High Speed Demonstrator Passive Le Bourget June 2013

SFWA-ITD overview Smart Passive Laminar Flow Wing § § Laminar Wing Ground test demonstrator to address structural, system and manufacturing aspects § 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 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 Large scale flight test demonstration of the laminar wing in operational conditions Port wing Laminar wing structure concept option 2 Laminar Wing aerodynamic layout and performance Le Bourget June 2013

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

Smart Wing flight test instrumentation Status March 2013 (ARM) exp A ecte d la min ar f low Extend of laminar flow A 340 -300 Smart Wing observation camera view angle from potential observer pod position (Airbus) Representation of laminar Wing on A 340 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) Le Bouget June 2013 B F In-Flight Monitoring of Wing Surface with Quasi tangential Reflectometry and Shadow Casting “WING REFLECTOMETRY” (FTI) 14

Working Principles v. 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 v 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

Smart Wing manufacturing and assembly scenarios Le Bourget June 2013 16

CROR demonstration engine Flying Test Bed Le Bourget June 2013 17

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

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