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


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:


SFWA-ITD overview


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


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 ?


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



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


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


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


SFWA-ITD overview


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



Smart Wing manufacturing and assembly scenarios

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CROR demonstration engine Flying Test Bed


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

Smart Fixed-Wing Aircraft

Documents