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Smart Fixed-Wing Aircraft

Smart Fixed-Wing Aircraft. SFWA-ITD overview. SFWA-ITD overview.  50% cut in CO2 emissions. Aircraft manufacturers 20-25%. Integration. Engine manufacturers 15-20%. Operations 5-10% Air Traffic Management.

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Smart Fixed-Wing Aircraft

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  1. Smart Fixed-Wing Aircraft

  2. SFWA-ITD overview

  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

  4. Input connectingto: • 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 • 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 Output providingdatato: TE– SFWA technologies for a Green ATS SFWA-ITD overview

  5. 3. Innovative Engine Demonstrator Flying Testbed Objective: Demonstrate viability of full scale innovative engine concept in operational condition Airbus A340-500 with modified wing SFWA-ITD ARM 2013 - SFWA-ITD overviewSFWA-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 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 DemonstrationDA Falcon F7X 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

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

  7. Active Flow Control: OverviewActive flow control system functionality testing AFLoNext CS2 ? Key message: Good AFC system performance demonstrated in ground tests for normal operation

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

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

  10. Control of loads and vibrations Simulations and demonstration strategy Validation plan in 2 steps • Phase 1: Ground Tests • Validation of control law designmethodology • Validation of ability to controlvibrations due to a well knownexcitation force • Phase 2: Flight Tests • Validation of vibration reductionfunction in real environment

  11. High Speed Demonstrator Passive

  12. Starboard wing Laminar wing structure concept option 1 Port wing Laminar wing structure concept option 2 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 Laminar Wing Ground test demonstrator to address structural, system and manufacturing aspects

  13. SFWA-ITD overview BLADE Partnership (Wing Perimeter)

  14. Smart Wing flight test instrumentation Status March 2013 (ARM) B E D F A C expected laminar flow 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 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) Phase locked PIV for quantitive wake-flow diagnostics of CROR-blades in flight (Illustration: DLR, 2009)

  15. 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

  16. Smart Wing manufacturing and assembly scenarios

  17. CROR demonstration engine Flying Test Bed

  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

  19. Thank you for your attention

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