· \r REG IADP Full Scale Demonstrators Master Plan –Major Milestones and TRL evolution R R))...

$Page 1: · \r REG IADP Full Scale Demonstrators Master Plan –Major Milestones and TRL evolution R R)) DEMONSTRATOR 2016 2017 2018 2019 2020 2021 2022 TRL3 TRL4 TRL5 TRL6$
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Title

Innovation Takes Off

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Title


REG IADP

January 2020

Clean Sky 2 Information Day dedicated to the

11th Call for Proposal (CfP11)

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From Clean Sky towards Clean Sky 2

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• CS2 REG IADP objective is to bring the integration of technologies for regional

aircraft to a further level of complexity and maturity than achieved in Clean Sky

GRA. The global strategy is to integrate and validate, at a/c level, advanced

technologies for regional aircraft so as to drastically de-risk their integration on

future products:

Leonardo Aircraft:

Airbus DS:

Notes:(*) Preliminary studies started in 2019

(**) Activities completed in 2019

TP130 Pax (**)Hybrid-Electric 40-50 Pax (*)TP 90 Pax

Multimission TP 70 Pax

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REG IADP TEAM

• LEADERS:

AG2CIRA, ONERA, IMAST (*),

HAI,SICAMB, SISW,

FOXBIT (*), AEROSOFT,

ITALSYSTEM, UMBRA,

NOVOTECH, TECNAM,

POLIMI, POLITO, UNINA,

UNIPI

UMBRA, CERTIA,

INSA, MAGNAGHI

AER., POLITO, VIOLA

IRON CIRA, CENAERO

NLR, ONERA, GRC,

DOWTY GE, AVIO GE,

TUD, POLITO, UNINA

ACITURRI, MTC,

CAETANO AER.

• CORE PARTNERS:

• Service Support:

(*) participation terminated in 2018-2019

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REG IADP Major Demonstrators

D1 – Adaptive Wing Integrated Demonstrator(Leader: Leonardo Aircraft)D1.1 – FLYING TEST BED#1 (FTB#1)Demonstration of LC&A and Aerodynamics enhancements features through new generation wing devices and advanced FC Actuation systems

D2 – Flying Test Bed #2 (FTB#2)(Leader: Airbus DS)

Integrated Technologies DemonstratorFlight Demonstration of a high efficient and low noise Wing with Integrated Structural and related Systems solutions

D3 - Fuselage / Cabin Ground Demonstrator (Leader: Leonardo Aircraft)Full scale composite fuselage and passenger cabin with innovative structural and architectural solutions aimed to weight and cost reduction , methodologies and technologies for innovative NDI, repair and maintenance, human centeredapproach, comfort

Flight Simulator

D4 - IRON BIRD Ground Demonstrator (Leader: Leonardo Aircraft )Integration and validation of FCS Load Control/Load Alleviation (LC/LA), Electrical Landing Gear, Electrical Power Distribution System, inter-system integration activity; support the achievement of the permit-to-fly for FTB#1)

D1.2 – OWB Ground Demonstrator Structural static and fatigue tests of innovative low cost and low weight structural technologies integrated at full scale level

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REG IADP Full Scale Demonstrators Master Plan – Major Milestones and TRL evolution

PDR

CDR

FT (Demo Flights)

GT (Demo Gnd Tests)

DEMONSTRATOR 2016 2017 2018 2019 2020 2021 2022

TRL3 TRL4 TRL5 TRL6

TRL4

TRL3 TRL4 TRL5 Step1 -TRL6

TRL4 TRL5 TRL6

TRL4 TRL5 TRL6

TRL3 TRL4 TRL5

2023

TRL5

D3.2 -Pax Cabin

D4 - Iron Bird

D1.1 - Flying Test Bed#1 (FTB1)

D1.2 - Outer Wing Box (OWB)

D2 - Flying Test Bed#2 (FTB2)

D3.1 - Fuselage Structure

Step2 -TRL6

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WBS REG IADP

WP 0.6 – Interfaces

WP 0.3 - Risks

WP 1.3Technologies Requirements

WP 0.4 - Quality

WP 2.4Innovative FCS

WP 0.5 – Disseminat.

WP 0.1 – Program WP 1.1 (*)Innovative A/C Configurations

WP 4.1Technology Assessment

WP 0.2 – Contracts

WP 1.2Top Level A/C Requirements

WP 4.2Ecodesign Interface

WP 2 TECHNOLOGIES DEVELOPMENT

WP 1 HIGH EFFICIENCY

REGIONAL A/C

WP 2.2Regional Avionics

WP 2.1Adaptive Electric

Wing

WP 3DEMONSTRATIONS

WP 4 TECHN. DEV. / DEMOs

RESULTS

WP 0 MANAGEMENT

WP 2.3Energy Optm. Regional A/C

WP 3.4Iron Bird

WP 3.5Integr. Tech. Demo.

(FTB2)

WP 3.1Adaptive Wing

Integrated Demo.

WP 3.2Fuselage / Cabin

Ground Demo

WP 0.7 – CPs

LDO VEL, CASA LDO VEL LDO VEL LDO VEL, CASA LDO VEL

Leonardo Aircraft (LDO VEL)

LDO VEL, CASA

LDO VEL

LDO VEL

LDO VEL

LDO VEL

LDO VEL

LDO VEL, CPs

LDO VEL, IRON

LDO VEL,LTS,ASTIB,IRON

LDO VEL, AG2, FhGLDO VEL, AG2

LDO VEL, CASA

LDO VEL

LDO VEL, ASTIB

LDO VEL

LDO VEL

LDO VEL, ASTIB

LDO VEL, ASTIB

LDO VEL, FhG

CASA, EWIRA

(*) CfP11 REG Topic is within WP1.1.3

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JTI-CS2-2020-CFP11-REG-01-20

Aerodynamics experimental characterization and new experimental testing methodologies for distributed electrical

propulsion

WP Location: REG IADP - WP 1.1.3

Objectives:

It is proposed to develop technologies for experimental assessment of DistributedElectrical Propulsion (DEP) aerodynamics and perform wind tunnel tests on a DEPconfiguration using as reference a regional 40 Pax aircraft.

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JTI-CS2-2020-CFP11-REG-01-20

OBJECTIVES:Distributed electrical propulsion (DEP) can be used to improveaircraft high lift performance. If properly designed DEP allows for anincrease of take-off and landing maximum lift coefficient thereforeresulting on a reduction of wing surface and aircraft weight.

The main objective of this CfP is to improve the physicalunderstanding of DEP technology for hybrid electrical aircraft:

Perform basic experimental studies to understand how DEPpropeller slipstream can increase airfoil maximum lift coefficient

Identify experimental techniques suited for DEP experimental test

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JTI-CS2-2020-CFP11-REG-01-20

It is proposed to test a 2D wing section, equipped with flap, andwith at least three propellers installed in front of the wing.

The wind tunnel experimental test should be aimed atmeasurement on the central wing section lift, drag and momentof:

Propeller thrust Propeller tip-vortex strength Propeller relative position Propeller diameters Flap setting

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JTI-CS2-2020-CFP11-REG-01-20

REQUIREMENTS:

Wing forces have to be measured separately from propeller forces. Internalbalance can be used, but alternative solutions can be proposed by theapplicant

it is necessary to measure force and moment of the wing section in the wakeof a single propeller in a DEP configuration.

Surface pressure measurements should be conducted with a sufficient span-wise and chord-wise density to accurately determine where stall is initiating.

The applicant could also propose additional experimental technics for betterunderstanding of flow behind the propeller and the flap and identify flowseparation regions (e.g. PIV, oil flow, Pressure sensitive paint). All thesemeasurements techniques are not mandatory but will be considered as anadded value to the proposal.

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JTI-CS2-2020-CFP11-REG-01-20

Full scale reference configuration

The reference configuration is a 40 seats regional aircraft. Theactual configuration design is not yet available, but it will beprovided before the project kick-off.

Anyway the provisional expected main characteristics of thefull scale configuration will be as follows:

Chord: 2.20 m Flap: single slotted flap (15° and 30°) Speed: 60 m/s Propeller thrust: 750 N, 1250 N, 1900 N Propeller diameters: 0,8 m, 1,3 m, 2,04 m Reynolds number based on chord: about 9 millions

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It is expected that scaled test article will have a chord not lower than 0,8 m andthat the test should reproduce a Reynolds number of about 3.5 Million.

Nevertheless, to remain within the budget limitation, the applicant can propose asmaller model scale and a smaller Reynolds number. In that case, evaluation of expecteduncertainties in the results should be provided.

The selected wind tunnel and model size should avoid blockage effect and wall/end platenegative interaction effect specially at high incidence and flap deflected.

The applicant has to:

1. Propose the best suited experimental arrangement and test article scale2. Design and manufacture the test article3. Provide engine and propellers4. Perform wind tunnel test and measurement5. Perform wind tunnel test data-analysis

JTI-CS2-2020-CFP11-REG-01-20

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JTI-CS2-2020-CFP11-REG-01-20

The following measurements/instrumentation is expected:

• Total forces and moments on the model measured by internal balance (Lift, Drag, Pitching) on the model central part;

• At least 100 steady pressure taps on the model central section in two lines at propeller side in the propeller wake;

• Propeller forces (Thrust and torque) on the central propeller measured with a maximum resolution of 1 % of the mean thrust;

• Propeller rotation speed, measured with a resolution of maximum 0.1% of the setpoint.;

• Propeller shaft power;

• Sufficient repeat measurements should be conducted to quantify errorbars in the delivered data.

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JTI-CS2-2020-CFP11-REG-01-20

ESSENTIAL TEST MATRIX

# FLAP Alpha Thrust Speed m/s

Flap gap/Overlap

Wing/propeller position

Propeller diameters

1 0° From -2 to stall

0 (no propellers, no nacelles)

60 Nominal N/A N/A



60 Nominal N/A N/A



60 Nominal N/A N/A


T1, T2, T3 60 Nominal Nominal Nominal






T2 40 Nominal Nominal Nominal


T2 40 Nominal Nominal 2 additional diameters

ADVANTAGEOUS TEST MATRIX

A1 15° From -2 to stall

T2 60 Nominal 4 positions Nominal




T2 60 Gap/overlap sensitivity

Nominal Nominal



Nominal Nominal



PROPOSED TEST MATRIX: MANDATORY PART

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JTI-CS2-2020-CFP11-REG-01-20

ESSENTIAL TEST MATRIX


Flap gap/Overlap


Propeller diameters



60 Nominal N/A N/A



60 Nominal N/A N/A



60 Nominal N/A N/A


















Nominal Nominal



Nominal Nominal



PROPOSED TEST MATRIX: OPTIONAL PARTESSENTIAL TEST MATRIX


Flap gap/Overlap


Propeller diameters



60 Nominal N/A N/A



60 Nominal N/A N/A



60 Nominal N/A N/A


















Nominal Nominal



Nominal Nominal



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JTI-CS2-2020-CFP11-REG-01-20

Tasks description:

WP1: ManagementThe applicant has to set-up all classical project management structure and will be required to organize periodic meetings (also by TELECON) with topic manager for project monitoring.

WP 2: Test set-up and test matrix• The following parameters have to be addressed:

– Two free stream speed

– Three propeller thrust levels test

– Four propeller/wing relative position

– Three propeller diameters

– Two flap settings (with possible gap/overlap experimental optimization at least for one single propeller power setting)

– A drag increase device for landing configuration

– Angle of attack up to stall plus 4° degrees

• To evaluate propeller installation effects, in addition to propeller-on tests, tests have to be performed also with propeller-off configuration and nacelle off configuration (only wing, that is, without nacelle and without propellers).

•

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JTI-CS2-2020-CFP11-REG-01-20

Tasks description:

WP 3: Wind tunnel model design and manufacturing• The applicant will be responsible to design and manufacture the model and provide all

required test instrumentation. The test article should have a chord not lower than about 0,8 meter (about 1 to 2,5 scale). Different scale model could be proposed depending on budget requirements.

• The following requirements are expected to be satisfied:

– Propeller blade pitch (fixed pitch) set with an accuracy of 0.05 degree

– Surface roughness between 0.3 and 0.4 mu meter

– Angle of attack of the model within 0.02 degree

WP 4: Wind tunnel test performance• The applicant will be responsible for test execution and to provide test engineering.

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JTI-CS2-2020-CFP11-REG-01-20

Tasks description:

WP 5: Wind tunnel test data-analysis

• The applicant will be responsible of test data analysis. Raw data processing and wind tunnel correction compliance with wind tunnel expertise have to be provided.

• The applicant has also to provide forces and moment acting on the wing central part without propeller forces.

• Therefore the following separated data-set have to be provided for each test conditions:

– Propeller forces, moment and power

– Central wing forces and moment

– Flap moment and forces (only for deflected flap configuration).

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JTI-CS2-2020-CFP11-REG-01-20

Major Deliverables:

Milestones (when appropriate)

Ref. No. Title - Description Type* Due Date

M1 (WP2) Experimental set-up definition R T0+6

M2 (WP3) Test article design R T0+9

M3 (WP3) Test article manufacturing H T0+18

M4 (WP4) Performance of wind tunnel tests D T0+20

M5 (WP5) Test report R T0+24

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JTI-CS2-2020-CFP11-REG-01-20

Milestones:

Deliverables

Ref. No. Title - Description Type* Due Date

Del 1.1 Technical Progress report R T0+12

Del 1.2 Final Technical Progress R T024

Del 2.1 Experimental set-up definition R T0+6

Del 2.2 Wind tunnel test matrix and test requirements R T0+6

Del 3.1 Test article design R, D T0+9

Del 3.2 Test article manufacturing H T0+18

Del 4.1 Preliminary Test report (raw data) R, D T0+20

Del 5.1 Final Test report (corrected data) R, D T0+24

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JTI-CS2-2020-CFP11-REG-01-20

Special Skills:

• Essential:– Managing capabilities for European research projects.

– Consolidated experience in wind tunnel test technical management.

– Knowledge of wind tunnel test measurement techniques.

– Experience in Wind tunnel test activities, data analysis and reporting.

• Advantageous:– Past expertise in propeller wind tunnel test

– Expertise in PIV/PSP measurement techniques

Indicative Funding Topic Value: 800 K€

Duration of the action: 24 Months

Type of Agreement: Implementation Agreement

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Title

Any questions?

[email protected]


Last deadline to submit your questions: 13 March 2020, 17:00 (Brussels time)

mailto:[email protected]

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Thank You

Disclaimer

The content of this presentation is not legally binding. Any updated version will be regularly advertised on the website of the Clean Sky 2 JU.

http://www.fraunhofer.de/de.html

http://www.fraunhofer.de/de.html

http://www.safran-group.com/?lang=fr

http://www.safran-group.com/?lang=fr

http://www.thalesgroup.com/

http://www.thalesgroup.com/

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