innovation takes off - clean skycleansky.eu/sites/default/files/documents/4- cs2cpw03id - overview...

Innovation Takes Off

Not legally binding


Clean Sky 2 Call for Core Partners

CP Wave 3 Overview of Call Topics

Michel Goulain, CS2 Project Officer

December 2015

2

List of Topics – LPA IADP

Not legally binding

List of Topics – LPA IADP

Not legally binding

LPA 01-08

LPA 01-09 LPA 01-10

List of Topics – FRC IADP

Not legally binding

List of Topics – FRC IADP

Not legally binding

FRC 01-01 FRC 02-03

FRC 02-06

FRC 02-04

FRC 02-05

List of Topics – AIRFRAME ITD

Not legally binding

TS A-0:

Management &

Interface

TS A-1:

Innovative

Aircraft

Architecture

TS A-2:

Advanced

Laminarity

TS A-3: High

Speed Airframe

TS A-4: Novel

Control

TS A-5: Novel

travel

experience

WP A-0.1 WP A-1.1 WP A-2.1 WP A-3.1 WP A-4.1 WP A-5.1

Overall

Management

Optimal engine

integration on

rear fuselage

Laminar nacelle

Multidisciplinary

wing for high &

low speed

Smart mobile

control surfaces

Ergonomic flexible

cabin


Business Aviation

OAD & config.

Mgt

CROR

configuration

NLF smart

integrated wing

Tailored front

fuselage

Active load

control

Office Centered

Cabin

WP A-0.3 WP A-1.3 WP A-2.3 WP A-3.3

LPA

OAD & config.

Mgt

Novel high speed

configuration

Extended

laminarity

Innovative shapes

& structure

WP A-0.4 WP A-1.4 WP A-3.4

Eco-Design

Managt & MPR

technologies

Novel certification

processes

Eco-Design for

airframe

A - High Performance and Energy

Efficiency

List of Topics – AIRFRAME ITD

Not legally binding

TS A-0:

Management &

Interface

TS A-1:

Innovative

Aircraft

Architecture

TS A-2:

Advanced

Laminarity

TS A-3: High

Speed Airframe

TS A-4: Novel

Control

TS A-5: Novel

travel

experience


Overall

Management

Optimal engine

integration on

rear fuselage

Laminar nacelle

Multidisciplinary

wing for high &

low speed

Smart mobile

control surfaces

Ergonomic flexible

cabin


Business Aviation

OAD & config.

Mgt

CROR

configuration

NLF smart

integrated wing

Tailored front

fuselage

Active load

control

Office Centered

Cabin

WP A-0.3 WP A-1.3 WP A-2.3 WP A-3.3

LPA

OAD & config.

Mgt

Novel high speed

configuration

Extended

laminarity

Innovative shapes

& structure

WP A-0.4 WP A-1.4 WP A-3.4

Eco-Design

Managt & MPR

technologies

Novel certification

processes

Eco-Design for

airframe


Efficiency

TS B-0:

Management &

Interface

TS B-1: Next

Generation

optimized wing

box

TS B-2:

Optimized high

lift

configurations

TS B-3:

Advanced

Integrated

Structures

TS B-4:

Advanced

Fuselage

WP B-0.1 WP B-1.1 WP B-2.1 WP B-3.1 WP B-4.1

Overall

Management

Wing for

incremental lift &

transmission shaft

integration

High wing / large

Tprop nacelle

configuration

Advanced

Integration of

syst. in nacelle

Rotor-less tail for

Fast Rotorcraft


SAT

OAD &

configuration Mgt

More affordable

composite

structures

High lift wing All electrical wing

Pressurized

fuselage for Fast

RotorcraftWP B-0.3 WP B-1.3 WP B-3.3 WP B-4.3

RotorCraft OAD &

configuration Mgt

More efficient

wings

technologies

Highly integrated

cockpit

More affordable

composite

fuselage

WP B-0.4 WP B-1.4 WP B-3.4 WP B-4.4

Regional a/c

OAD & config.

Mgt

Flow & shape

control

More affordable

small a/c

manufacturing

Affordable low

weight, human

centered cabinWP B-0.5 WP B-3.5

Eco-Design

Managt & MPR

technologies

Advanced

integration of

syst. in small a/cWP B-3.6

New materials &

manufacturing

B - High Versatility and Cost Efficiency

TS B-0:

Management &

Interface

TS B-1: Next

Generation

optimized wing

box

TS B-2:

Optimized high

lift

configurations

TS B-3:

Advanced

Integrated

Structures

TS B-4:

Advanced

Fuselage


Overall

Management

Wing for

incremental lift &

transmission shaft

integration

High wing / large

Tprop nacelle

configuration

Advanced

Integration of

syst. in nacelle

Rotor-less tail for

Fast Rotorcraft


SAT

OAD &

configuration Mgt

More affordable

composite

structures


Pressurized

fuselage for Fast


RotorCraft OAD &

configuration Mgt

More efficient

wings

technologies

Highly integrated

cockpit

More affordable

composite

fuselage

WP B-0.4 WP B-1.4 WP B-3.4 WP B-4.4

Regional a/c

OAD & config.

Mgt

Flow & shape

control

More affordable

small a/c

manufacturing

Affordable low

weight, human


Eco-Design

Managt & MPR

technologies

Advanced

integration of


New materials &

manufacturing


AIR 01-04

AIR 02-09 AIR 02-10 AIR 02-11

List of Topics – ENGINE ITD

Not legally binding

List of Topics – ENGINE ITD

Not legally binding

ENG 01-08

ENG 03-03 ENG 03-04

ENG 03-05

List of Topics – SYSTEMS ITD

Not legally binding

List of Topics – SYSTEMS ITD

Not legally binding

SYS 02-03 SYS 02-04 SYS 02-05

SYS 02-07 SYS 02-08

SYS 02-06

Questions ?

13

Any questions on the Call and topics can be

addressed to the following mailbox:

[email protected]

Deadline to submit questions: , 17:00

mailto:[email protected]










Not legally binding

Q&A

Thank You!

15

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

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

http://www.thalesgroup.com/

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.

Back up slides


LPA – IADP Presented by

Jens Koenig ; AIRBUS

Brussels, 8th of December 2015

Clean Sky 2 Information Day dedicated to the 3rd Call for Core Partners (CPw03)

From Clean Sky towards Clean Sky 2

CS1 Smart Fixed Wing Aircraft -ITD (SFWA)

Is a unique environment for high TRL integrated Research and Development

Provides the frame for well aligned objective driven R&T covering

development and maturation through numerical simulation,

rig demonstrators, wind tunnel testing, large scale and

flight testing under conditions relevant for operation

TRL6

TRL5

TRL4

CS2 Large Passenger Aircraft IADP (LPA)

Will provide a platform for even more focussed large scale, highly

integrated demonstrators with core partners and partners

Build on down best candidate technologies emerging from

CleanSky 1 other national and EU R&T programs and

additional technologies developed in CS2 ITDs

SFWA key technologies

o NLF – wing for large transport aircraft and

bizjets

o CROR engine integration

o Innovative empennage for next generation

bizjets

o Innovative control surfaces

o Buffet Control Technologies

o Advanced load control architectures and

function

o Advanced Flight Test instrumentation

2 3 4 5 6

Contribute to TRL - Scale

1

TRL3

CS2 Info Day CPw03, Brussels, 08.Dec.2015

Setup and Implementation

rr

Platform 1 Advanced Engine and

Aircraft Configuration

Platform 2 Innovative Physical

Integration Cabin-System-

Structure

Platform 3 Next Gen. A/C Systems,

Cockpit Systems &

Avionics

„Mature and validate disruptive

technologies for next generation

Large Passenger Aircraft through

large scale integrated

demonstration“



WP 0

LPA – IADP

WP 0.1

Technology assessment

WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0

Advanced Engine & Aircraft Configuration

WP 1.1

CROR Demo engine FTD

WP 1.2

Advanced engine integration driven fuselage

WP 1.3

Validation of scaled flight testing

WP 1.4

Hybrid Laminar Flow Control large scale demonstration

WP 1.5

Applied technologies for enhanced aircraft performance

WP 1.6

Demonstration of radical aircraft configurations

Platform 2 – WP 0

Innovative Physical Integration Cabin-System-Structure

WP 2.1

Integrated product architecture

WP 2.2

Non-specific design technologies

WP 2.3

Technology validation

Platform 3 – WP 0

Next generation Aircraft, Cockpits Systems & Avionics

WP 3.1

Enhanced flight operations & functions

WP 3.2 Innovative enabling technologies

WP 3.3

Next generation cockpit functions flight demonstration

WP 3.4

Enhanced cockpit demonstration

WP 3.5

Disruptive cockpit demonstration

WP 3.6

ADVANCE (Maintenance)

LPA-IADP Work Breakdown Structure

Overview of the LPA-CfP03 topics

Platform 1

No topics for LPA Platform 2 and 3 in this call


SAFRAN

Airbus

Airbus


WP 0

LPA – IADP

WP 0.1


WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5


WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1



WP 3.3


WP 3.4


WP 3.5


WP 3.6

Maintenance


LPA-IADP WBS – “Platform 1”

Estimated Volume of Activities ~560M€

Next Gen. A/C Systems, Cockpit Systems & Avionics

Advanced Engine and Aircraft Configurations


Large Passenger Aircraft Platform – integration topics

TRL 4-6 Aircraft Level

Airbus with SAAB, Dassault,

SNECMA and Partners

Platform 1 Advanced Engine and Aircraft Configurations

WP 1.1 CROR demo engine FTD

WP 1.2 Advanced engine integration driven rear fuselage

WP 1.3 Validation of scaled flight testing

WP 1.4 Hybrid laminar flow control large scale demonstration • HLFC applied on fin in long-term flight operation

• HLFC wing pre-flight demonstrator

WP 1.5 Applied technologies for enhanced aircraft performance

WP 1.6 Demonstration of radical aircraft configurations



WP 0

LPA – IADP

WP 0.1

Technology assessement

WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5

Innovative Flight Operations

WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1


WP 3.2 Avionic backbone technologies

development, integration & demonstration

WP 3.3


WP 3.4

Next generation cockpit ground demonstrator

WP 3.5

Pilot Case Demonstrator

WP 3.6

Maintenance








Airbus with, Liebherr,

Fraunhofer and Partners

Platform 2 Innovative Physical Integration Cabin-System-Structure

WP 2.1 Integrated product architecture

WP 2.2 Non specific design technologies

WP 2.3 Technology validation

WP 2.3.1 Multi purpose demonstrators

• Next generation fuselage, cabin & cargo functional demonstrator

• Next generation cabin & cargo functional demonstrator

• Next generation lower centre fuselage structural demonstrator

WP 2.3.2 Testing

WP 2.3.3 Pre-Production Line Technologies

CS2 Info Day CPw03, Brussels, 08.Dec.2015 Estimated Volume of Activities ~290M€

WP 0

LPA – IADP

WP 0.1


WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5


WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1



WP 3.3


WP 3.4


WP 3.5


WP 3.6

Maintenance



Setup and Implementation LPA Platform 3


Next Gen. A/C Systems, Cockpit & Avionics



Large Passenger Aircraft Platform – integration topics TRL 4-6 Aircraft Level

Airbus with Thales, Liebherr,

SAFRAN and Partners

Platform 3 Next Gen. Aircraft A/C Systems, Cockpits & Avionics

WP 3.1 Enhanced flight operations and functions


WP 3.3 Next generation cockpit functions flight demonstration

WP 3.4 Enhanced cockpit demonstrator

WP 3.5 Disruptive cockpit demonstration

WP 3.6 Maintenance

Cockpit of the future (Fenics)



Platform 1



SAFRAN

Airbus

Airbus


WP 0

LPA – IADP

WP 0.1


WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5


WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1



WP 3.3


WP 3.4


WP 3.5


WP 3.6

Maintenance

Assignment of the LPA-CPw03 topics

LPA

01-08

LPA

01-09

LPA

01-10


LPA – IADP Presented by

Jens Koenig ; AIRBUS

Brussels, 8th of December 2015

Clean Sky 2 Information Day dedicated to the 3rd Call for Core Partners (CPw03)


CS1 Smart Fixed Wing Aircraft -ITD (SFWA)

Is a unique environment for high TRL integrated Research and Development

Provides the frame for well aligned objective driven R&T covering

development and maturation through numerical simulation,

rig demonstrators, wind tunnel testing, large scale and

flight testing under conditions relevant for operation

TRL6

TRL5

TRL4

CS2 Large Passenger Aircraft IADP (LPA)

Will provide a platform for even more focussed large scale, highly

integrated demonstrators with core partners and partners

Build on down best candidate technologies emerging from

CleanSky 1 other national and EU R&T programs and

additional technologies developed in CS2 ITDs

SFWA key technologies

o NLF – wing for large transport aircraft and

bizjets

o CROR engine integration

o Innovative empennage for next generation

bizjets

o Innovative control surfaces

o Buffet Control Technologies

o Advanced load control architectures and

function

o Advanced Flight Test instrumentation

2 3 4 5 6

Contribute to TRL - Scale

1

TRL3


Setup and Implementation

rr

Platform 1 Advanced Engine and

Aircraft Configuration

Platform 2 Innovative Physical

Integration Cabin-System-

Structure

Platform 3 Next Gen. A/C Systems,

Cockpit Systems &

Avionics

„Mature and validate disruptive

technologies for next generation

Large Passenger Aircraft through

large scale integrated

demonstration“



WP 0

LPA – IADP

WP 0.1


WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5


WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1



WP 3.3


WP 3.4


WP 3.5


WP 3.6

ADVANCE (Maintenance)



Platform 1



SAFRAN

Airbus

Airbus


WP 0

LPA – IADP

WP 0.1


WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5


WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1



WP 3.3


WP 3.4


WP 3.5


WP 3.6

Maintenance









Airbus with SAAB, Dassault,

SNECMA and Partners

Platform 1 Advanced Engine and Aircraft Configurations

WP 1.1 CROR demo engine FTD

WP 1.2 Advanced engine integration driven rear fuselage

WP 1.3 Validation of scaled flight testing

WP 1.4 Hybrid laminar flow control large scale demonstration • HLFC applied on fin in long-term flight operation

• HLFC wing pre-flight demonstrator

WP 1.5 Applied technologies for enhanced aircraft performance

WP 1.6 Demonstration of radical aircraft configurations



WP 0

LPA – IADP

WP 0.1

Technology assessement

WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5

Innovative Flight Operations

WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1


WP 3.2 Avionic backbone technologies

development, integration & demonstration

WP 3.3


WP 3.4

Next generation cockpit ground demonstrator

WP 3.5

Pilot Case Demonstrator

WP 3.6

Maintenance








Airbus with, Liebherr,

Fraunhofer and Partners

Platform 2 Innovative Physical Integration Cabin-System-Structure

WP 2.1 Integrated product architecture

WP 2.2 Non specific design technologies

WP 2.3 Technology validation

WP 2.3.1 Multi purpose demonstrators

• Next generation fuselage, cabin & cargo functional demonstrator

• Next generation cabin & cargo functional demonstrator

• Next generation lower centre fuselage structural demonstrator

WP 2.3.2 Testing

WP 2.3.3 Pre-Production Line Technologies

CS2 Info Day CPw03, Brussels, 08.Dec.2015 Estimated Volume of Activities ~290M€

WP 0

LPA – IADP

WP 0.1


WP 0.2

EcoDesign

WP 0.3

ITD - Interfaces

Platform 1 – WP 0


WP 1.1


WP 1.2


WP 1.3


WP 1.4


WP 1.5


WP 1.6


Platform 2 – WP 0


WP 2.1


WP 2.2


WP 2.3


Platform 3 – WP 0


WP 3.1



WP 3.3


WP 3.4


WP 3.5


WP 3.6

Maintenance



Setup and Implementation LPA Platform 3


Next Gen. A/C Systems, Cockpit & Avionics



Large Passenger Aircraft Platform – integration topics TRL 4-6 Aircraft Level

Airbus with Thales, Liebherr,

SAFRAN and Partners

Platform 3 Next Gen. Aircraft A/C Systems, Cockpits & Avionics

WP 3.1 Enhanced flight operations and functions


WP 3.3 Next generation cockpit functions flight demonstration

WP 3.4 Enhanced cockpit demonstrator

WP 3.5 Disruptive cockpit demonstration

WP 3.6 Maintenance

Cockpit of the future (Fenics)



Platform 1



SAFRAN

Airbus

Airbus

CPW03-LPA-01-09 ‘INCO’


• JTI-CS2-2015-CPW03-LPA-01-09 Type:RIA

• Title: Aircraft Configuration Studies and Demonstration (Scaled Flight Testing, Instrumentation)

• Objective: Under this task, Aircraft configuration studies (focus on Hybrid Electric Propulsion) are to be performed. For the demonstration of new configurations Scaled Flight Testing is to be validated (with focus on Instrumentation). The major part of activity relates to the design of the Alternative Energy Propulsion Architecture & Components (i.e Divergent Aircraft Configuration) and the demonstration of resulting configurations.

• Volume: 4000k€ funding

WP 1.6.1 Alternative Energy Propulsion Architecture & Components

WP 1.6 Demonstration of Radical Aircraft

Configurations

WP 1.6.3 Radical Configuration

Flight Test Demonstrator

WP 1.6.2 Hybrid Power Bench

Development & Testing

WP 1.6.4 Flight Testing of

Large UHBR Engine

WP 1.6.5 Evaluation of Overall

Architecture/Configuration



Scaled Flight Testing – Test Aircraft Instrumentation (WP1.3.4) Development and build of the Flight Test Instrumentation (FTI) and matching ground equipment (ground station) for the validation of Scaled Flight Testing.

Alternative Energy Propulsion Architecture & Components – Divergent Aircraft Configuration (WP1.6.1) Under this WP a conceptual aircraft configuration exercise will be performed, sketching up different aircraft concepts from the Large Passenger Aircraft sector.

Deliverables

Ref. No. Title - Description Type Due Date

D-1.3.4-1 Matured Test Instrumentation (based on

IEP)

D T0+6

D-1.3.4-2 Test Instrumentation Review & Report RM T0+15

D-1.3.4-3 Modified Test Instrumentation (based on

FT)

D T0+18

D-1.3.4-4 Modified Test Instrumentation Review &

Report

RM T0+30

Deliverables


D 1.6.1.5-04 Concepts proposal RM T0+12

D 1.6.1.5-07 Concepts from 1st loop RM T0+24

D 1.6.1.5-10 Concepts, 2nd loop RM T0+36

D 1.6.1.6-01 (contribution to) Validation &

Verification Plan for Demonstrator

R T0+48

D 1.6.1.6-02 (contribution to) Conceptual

Engineering Review (CER)

RM T0+54

D 1.6.1.6-03 (contribution to) Preliminary Design

Review (PDR)

RM T0+60

D 1.6.1.6-04 (contribution to) Critical Design Review

(CDR)

RM T0+66

D 1.6.1.6-04 (contribution to) Components available D T0+72



Field of required experience

• instrumentation for remotely controlled vehicles for

dynamically scaled Flight testing / Radical Aircraft

Configurations

• test instrumentation for various flight physics related

parameters, including the identification of flight

dynamics

• experience in conceptual aircraft design studies for

Large Passenger Aircraft, including multi-disciplinary

optimisation

CPW03-LPA-01-10 ‘PROPEL’


• JTI-CS2-2015-CPW03-LPA-01-10 Type:RIA

• Title: Aircraft and Hybrid Propulsion System Architecture, Integration and Verification

• Objective: The current proposal is aimed at development of tools and methods for design, optimisation and verification of various hybrid propulsion systems and their integration into a new radical aircraft configuration that will be developed and demonstrated in WP1.6 of LPA IADP.

• Volume: 5000k€ funding

WP 1.6.1 Alternative Energy Propulsion Architecture & Components

WP 1.6 Demonstration of Radical Aircraft

Configurations

WP 1.6.3 Radical Configuration

Flight Test Demonstrator

WP 1.6.2 Hybrid Power Bench

Development & Testing

WP 1.6.4 Flight Testing of

Large UHBR Engine

WP 1.6.5 Evaluation of Overall

Architecture/Configuration



Workstream Task Contribution to the development of a scaled flight testing vehicle

Focus on Development and implementation of a Guidance system

Conceptual aircraft designs of novel configuration, with Hybrid Electric Propulsion system

Design space popultation

Design of novel propulsors utilizing hybrid drive

Design and validation of fans exposed to high levels of inlet flow distortions Assessment of noise signatures for novel propulsor installations Development of advanced analytical tool for effectiveness of propulsors integrated into radical aircraft configurations Development, validation and demonstration of electrical power systems for hybrid propulsion Novel intake or nacelle aerodynamics and demonstration of separation suppression in adverse pressure gradient regions Development of integrated thermal management systems



Design and integration of novel propulsors

Interaction between different workstreams and tasks



Required Skills • Demonstrated experience in conceptual aircraft design • Capability in computational modelling and experimental testing of various propulsor

solutions (ducted and unducted fans with or without inlet distortions). • Experience in aeromechanical design and optimisations of such fans. • Experience in assessing noise propulsor/engine noise signatures and potential

operational limitations especially related to takeoff and approach phases of flight. • Experience in analytical, computational and experimental assessments of various aircraft-

propulsor-engine configurations and method. Access to or plans to develop tools to allow novel design optimisations.

• Experience in electrical power systems to provide electrical power system architecture and specifications as well as both steady state and transient modelling capability. It is essential that the partners have existing methods to validate higher voltage implications and overall integrated aerospace power and propulsion test rigs to validate control strategies. It is desirable that partners have other subscale rigs and demonstrators to support the programme.

• Experience in guidance systems for scaled vehicles for Dynamically Scaled Flight Testing / Radical Aircraft Configurations

Clean Sky 2 Information Day dedicated to the

2nd Call for Partners (CfP02)


ITD Systems

Brussels, September 3rd, 2015

Not legally binding

JTI-CS2-2015-CFP02-SYS-02-01 : High brightness microdisplay system

for Head Up Displays - Scope and objectives

Context and applications :

Future Eyes out applications in cockpits require a new generation of emissive micro-displays with full color, very high brightness, low power and good form factor capabilities

Technical Target in the project: - Innovative solutions such as emissive micro-displays based on arrays of color LEDs structured on

sapphire wafers and coupled to a silicon backplane active matrix - Main characteristics :

- Maximum brightness : at least of 1.000.000 cd/m² and possibly 10.000.000 cd/m² - Targeted Resolution : 1920x1200 pixels (WUXGA) - Die Size ~ 1’’ diagonal (inducing a Pixel pitch ~ 8-10µm) - Spectral Bandwidth < 50 nm - Selected half angle of emission ~ 30°

Timeframe and funding:

Foreseen start : mid-2016 Indicative Funding Topic Value Foreseen end : end-2019 3800K€

©THALES

Not legally binding

JTI-CS2-2015-CFP02-SYS-02-01 : High brightness microdisplay system

for Head Up Displays - WBS

WP1 Development of monochromatic emissive materials and

optimisation of their optical efficiency.

WP2 Development of array structuration process or deposition

process.

WP3 Design of color Active Matric backplane compatible with

monochromatic applications.

WP4 Research of solutions for high brightness full color applications

with optimized optical efficiency.

WP5 Design and manufacture of emissive monochrome green micro-

display prototypes

WP6 Design and manufacture of emissive full color micro-display

prototypes

WP7 Development of micro-display mother-Board and complete

characterisation of developed components

Proposed WBS To be refined by applicant

Not legally binding

JTI-CS2-2015-CFP02-SYS-02-02 : Passive thermo-acoustic insulation for small aircraft

Context and applications : Content is focused on the development of passive noise reduction insulation and heat insulation as complex material required by small aircraft producers. The development activity is focused on decreasing of noise level during cruising speed regime and stable heat comfort. The aim is demonstrator of complex acoustic and heat insulation installed inside aircraft fuselage.

Technical Target in the project: • Selection of optimal materials with requested structure • Design of samples (separately for noise and heat insulation) for testing in laboratory and real conditions • Design of demonstrator final parts and their application on the fuselage panels (complex material structure or

sandwiches structure for noise and heat insulation with standards FAR) - Main characteristics :

- Testing should cover this materials: porosity polymers, fibres structure, adhesive systems, AL foils, plastics, etc.) and typically materials used on the walls of fuselage aircrafts

- Tests are focused on SPL with dynamic range 50 – 110dB / f = 20 – 12500Hz, SPL eq = 50-65dB. - Vibration on walls: D walls = 1-5dB, f = 50 – 1000Hz/vibration tests. - Material structure: optimal porosity, density, mechanical properties, adhesive ability, self-extinguishing, weight, etc)


Foreseen start : Q1/2016 Indicative Funding Topic Value Foreseen end : Q1/2019 400K€

Not legally binding

JTI-CS2-2015-CFP02-SYS-02-02 : Passive thermo-acoustic insulation for small aircraft


Deliverables


D1 Typical materials research study and selection of materials for

testing R and RM T0 + 4 month

D2 Research study of optimal testing methods and type of samples

R T0 + 4 month

D3 Test and test evaluation progress report R and RM T0 + 10 month

D4 Test report and calculating review R and RM T0 + 17 month

D5

Production and technological documentation, detailed material

specification (certification according to FAR/CS 23 included) TD T0 + 21 month

D6



D7 Demonstrator of normal passive insulation D T0 + 36 month

D8



D9 Demonstrator of optional passive insulation (TRL 3-4) D T0 + 36 month

D10 Delivery of sample series used for design of demonstrator TD T0 + 36 month

Not legally binding

JTI-CS2-2015-CFP02-SYS-02-03 : Database of dynamic material properties for selected materials commonly used in aircraft industry

Context and applications : In order to perform the simulation of complex crash behaviour of aircraft seat, with results close to the real behaviour during crash test, among other parameters, high speed dynamic material properties have to be used.

Technical Target in the project: - Selection of reasonable range of materials intended for testing - Creation of test methodology (Including design & manufacturing of specimens) for material high speed

testing - Performance of high speed material tests - Creation of material properties database which will be used as an input for crash simulations

- Main characteristics : - Testing should cover about 12 materials (Al, steel, composite, plastics, etc.) which are typically used in

aircraft industry - Coupon testing for expected strain rates from 5s-1 to 500s-1


Foreseen start : Q1/2016 Indicative Funding Topic Value Foreseen end : Q1/2017 300K€

Not legally binding

JTI-CS2-2015-CFP02-SYS-02-03 : Database of dynamic material properties for selected materials commonly used in aircraft industry


Deliverables


D1 Research study of typical material and selection of materials

for testing R and RM T0+2 month

D2 Research study of regulations for dynamic testing R T0+2 month

D3 Test specification and specimen design progress report R T0+3 month

D4 Test specification, test specimen drawings R and RM T0+4 month

D5 Specimen manufacturing progress report R T0+8 month

D6 Test and test evaluation progress report R T0+11 month

D7 Test evaluation report and material dynamic property

database R T0+13 month

Not legally binding

SYS-02-09 : ALGeSMo - Advanced Landing Gear Sensing & Monitoring

Context and applications :

ALGeSMo – is a system that will measure load at the landing gear to provide loads data for use on the aircraft systems for integration with aircraft health monitoring, hard landing detection, flight management and flight controls.

Technical Target in the project: • Integration of load and torque sensors into large passenger aircraft landing gear to provide robust,

accurate, reliable load measurement and the potential for health monitoring capability.

• The sensors will measure loads using optical Fibre Bragg Grating technology integrated into the landing gear using an Airbus patented method and compression of each landing gear shock absorber using rotary sensor

• Complete system development; system architecture definition, equipment specification, design, manufacture, system integration and tests.

• The aim of the project is to take a fully integrated system from post TRL-4 through to flight test on a single aisle aircraft and demonstrate of a working aircraft-integrated system at TRL 6.


Foreseen start : mid-2016 Indicative Funding Topic Value Foreseen end : Q3-2019 2400K€

Not legally binding

SYS-02-09 : ALGeSMo - Advanced Landing Gear Sensing & Monitoring

Expected high level roadmap

Not legally binding

JSYS-02-10 : Analysis of centrifugal compressor instabilities occurring

with vaneless diffusor, at low mass flow momentum

Context and applications : The performance of compressors at low mass-flows is characterized by the occurrence of unsteady flow phenomena surge and rotating stall. These instabilities can cause noise nuisance and critical operating conditions with strong dynamical loading on the blades. Such phenomena must be detailed with the aim of applying a flow control strategy to enlarge the operating range and / or improve the stage performances.

Technical Target in the project: • Validate of the numerical approach necessary to capture the unsteady feature of the flow at near surge

on an academic open reference case. • Determine a surge inception scenario on the industrial compressor ( [30,90] krpm, volute ~200mm),

using the validated numerical methodology, coupled with experimental measurement validation. • Investigate the influence of the volute tongue and it contribution to stall inception by numerical means • Provide an analytical study based on stability method, aiming at predicting the unstable modes and the

associated frequency and rotational speed early in the design process • Provide a low-CPU-cost numerical methodology (RANS, 2D, analytical, …) to assess surge line during

design phases derived from the above results


Foreseen start : mid-2016 Indicative Funding Topic Value Foreseen end : mid-2020 1125 K€

©THALES

Not legally binding


JSYS-02-10 : Analysis of centrifugal compressor instabilities occurring

with vaneless diffusor, at low mass flow momentum

Tasks

Ref. No. Title - Description Due Date

T01 Validation of the numerical approach on an academic open reference case

T0+24

T02 Surge inception on industrial case T0+42

T03 Volute geometry impact on performances T0+42

T04 Theoretical approach T0+48

Not legally binding

JSYS-02-11 : Innovative design of acoustic treatment for air conditioning

system

Context and applications : The air jet pump generates noise at the aircraft skin. High frequency noise reduction is achieved using passive treatment and some studies have been performed to improve the attenuation in middle and low frequencies with locally reacting materials. Some innovative solutions, highly efficient on an acoustic point of view, as well as light and compact, must therefore be developed.

Technical Target in the project: - Compact and low frequencies absorption concept proposal

- Implementation of a dedicated modal detection solution for jet pump noise source characterization

- Prototypes manufacturing for laboratory and final system level tests

- Main characteristics :

- Duct flow M=0.3

- Frequency range [100 – 5000] Hz

- Temperature ~ 150°C


Foreseen start : mid-2016 Indicative Funding Topic Value Foreseen end : mid-2019 670 K€

©THALES

Not legally binding


JSYS-02-11 : Innovative design of acoustic treatment for air conditioning

system

JTI-CS2-2015-CFP02-SYS-02-12 : Eco Design : Optimization of SAA

chromium free sealing process

Context and applications : Thin layer (≤5 µm) sealed SAA is a good alternative process to replace sealed CAA on aluminium unpainted parts. Previous studies performed by the Topic Manager covered: - Optimisation of the process parameters for SAA on AA2024 sheets and machined samples - Development of 2 sealing solutions (containing 5 and 3 chemicals components in a given concentration), yet optimisation is still required: promising results on AA2024 but implementation to other aluminium alloys, such as cast alloy AU5NKZr, requires further investigations.

Technical Target in the project: • To optimize the sealing processes previously developed for the given thin layer SAA (≤ 5 µm):

- To evaluate the effects of each component of the 2 sealing solutions on the corrosion performance on AA2024 sheet and machined samples.

- To optimize the concentration of the influent components and the sealing process parameters taking into account the economic and environmental aspects.

• To implement the full processes on other substrates widely used by the Topic Manager: AA2618, AU5NKZr, AS7G06.

• To transfer the processes to an industrial scale and to manufacture demonstrators (e.g. surface treatment of turbomachinery wheels, valve bodies…).

Timeframe and funding: Foreseen start: mid-2016 Indicative Funding Topic Value: Foreseen end: mid-2018 350k€

Proposed WBS:

Not legally binding

Task 1 Definition of the requirements

Task 2 Optimization of the sealing parameters

Task 3 Implementation of the optimized sealing solutions to other aluminium alloys

Task 4 Industrial up-scaling and demonstrators

Task 5 Characterisation of the samples and demonstrators

Special skills, Capabilities, Certification expected from the Applicant: • Strong experience on surface technologies, especially on chrome free surface treatments (SAA, sealing

processes) • Strong experience and knowledge on the surface treatments of the following alloys : AS7G06 and

AU5NKZr cast alloys, AA2618, and their corrosion behaviour after treatment and mechanisms involved. • Strong experience in the industrial up-scaling in the aeronautical field • Capacity and ability to implement in a pre-industrial and industrial scale, the processes developed during

the project • Capabilities required to performed the study:

– Laboratory (20-30L), pre-industrial (200-300L) and industrial (1000L) baths, – SEM-EDX, FIB, XRD, contact angles measurement – equipment for electrochemical analysis (especially Electrochemical Spectroscopy Impedance) – Salt Spray Test

JTI-CS2-2015-CFP02-SYS-02-12 : Eco Design : Optimization of SAA

chromium free sealing process

Not legally binding

SYS-02-13 : Analysis, validation and data collection of design and

operating parameters for advanced cabin ventilation concepts

related to future aircraft energy management systems

Context and applications : Future aircraft energy management systems, aiming at smart management of electric power and thermal loads at system level, will substantially impact the cabin fluid- and thermodynamics.

Due to the complex boundary conditions of cabin fluid- and thermodynamics, experimental validation

at full scale in cabin mock-ups and demonstrators are required.

Technical Target in the project: • Planning and design of a fully representative cabin mock-up in consideration of future long range

aircraft concepts, based upon airframer inputs

– Ventilation systems able to switch easily between various configurations, accurate control and measurement of all relevant mass flows and temperatures, considering the most valuable measurement techniques

• Preliminary design and numerical optimization of the cabin ventilation system

– Unsteady CFD and thermal comfort simulations on various cabin air flow systems,

– Preselection of promising ventilation system design and integration/ validation by mock up test, and further optimization.

• Experimental studies of cabin fluid- and thermodynamics related to future energy management systems

Timeframe and funding: Foreseen start : mid-2016 Indicative Funding Topic Value Foreseen end : Mid -2020 2 000K€

Not legally binding

SYS-02-13 : Analysis, validation and data collection of design and

operating parameters for advanced cabin ventilation concepts

related to future aircraft energy management systems

Expected high level roadmap

Deliverables

Ref. No. Title – Description Due Date

D_6.4.5_1 Planning document for used measurement

techniques and test matrix

T0+12 months

D_6.4.5_2 Design documentation of optimized

components

T0+18 months

D_6.4.5_3 Cabin mock up T0 +24 months

D_6.4.5_4 First validation results report T0 + 33 months

D_6.4.5_5 Processed measurement data and final

report

T0+48 months

Milestones

Ref. No. Title – Description Due Date

M_6.4.5_1 Specification of requirements for a future

long range cabin mock-up

T0+3 months

M_6.4.5_2 Planning and design freeze for cabin mock-up T0+12 months

M_6.4.5_3 Mock-up and measurement techniques ready

for testing, start of validation

T0+24 months

M_6.4.5_4 First validation results T0+33 months

M_6.4.5_5 Optimized hardware available T0+39 months

Clean Sky 2 Information Day

3rd Call for Core Partners (CPW03)

AIRFRAME ITD Yvon Ollivier (Dassault Aviation)

Brussels, 8th December 2015

70


71

Step changes in the “efficiency” of all airframe elements by the means of a systematic “re-thinking”

Re-think the a/c architecture

Re-think the fuselage

Re-think the wing

Re-think the control

Re-think the cabin

Smart Fixed Wing Aircraft

• Greener Airframe Technologies •More Electrical a/c architectures

• More efficient wing • Novel Propulsion Integration Strategy • Optimized control surfaces

• Integrated Structures • Smart high lift devices

Key Objectives • SUPPORT TO IADP: Maturate technologies up to TRL 6 through

integrated demonstrators performed mostly in IADPs for:

– More efficient airframe : drag, weight, cost, environmental impact, passenger well-being, maintenance, servicing, …

– Efficiency of the engineering & manufacturing process : time-to-market and competitiveness against low-cost labor countries,

• FUTURE: De-risk novel generation product in the prospect of changing step

by 2030+

– Introduction of innovative airframe architecture

– Investigate lower TRL technologies (e.g. HLFC, extended laminarity)

• TRANSVERSE: Progress on some transverse topics

– Full address of a technology issue from modeling to certification ability

– Eco-Design for airframe

72 Supporting a 5 Product’s Segments Strategy Base

CS2 Infoday - Toulouse 73

High Performance & Energy Efficiency (A) High Versatility & Cost Efficiency (B)

Innovative Aircraft

Architecture

Advanced Laminarity

High Speed Airframe

Novel Control

Novel travel

experience

Next generation optimized

wing

Optimized high lift configs.

Advanced integrated structures

Advanced Fuselage

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Advanced Manufact.

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Overall Technical Overview

04/09/2014 Tran

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Overall WBS and participants

74

5 Technology Streams 4 Technology Streams

Leaders: DAv, SAAB Participants: Airbus, Fraunhofer CP: NACOR, GAINS

Leaders: Airbus D&S S.A.U. (CASA) Participants: Airbus, Alenia, AW, A-H, Fraunhofer, SAAB, Evektor, Piaggio CP: NACOR, OUTCOME, ASTRAL, SHERLOC

TS A-0:

Management &

Interface

TS A-1:

Innovative

Aircraft

Architecture

TS A-2:

Advanced

Laminarity

TS A-3: High

Speed Airframe

TS A-4: Novel

Control

TS A-5: Novel

travel

experience

TS B-0:

Management &

Interface

TS B-1: Next

Generation

optimized wing

box

TS B-2:

Optimized high

lift

configurations

TS B-3:

Advanced

Integrated

Structures

TS B-4:

Advanced

Fuselage

WP A-0.1 WP A-1.1 WP A-2.1 WP A-3.1 WP A-4.1 WP A-5.1 WP B-0.1 WP B-1.1 WP B-2.1 WP B-3.1 WP B-4.1

Overall

Management

Optimal engine

integration on

rear fuselage

Laminar nacelle

Multidisciplinary

wing for high &

low speed

Smart mobile

control surfaces

Ergonomic flexible

cabin

Overall

Management

Wing for

incremental lift &

transmission shaft

integration

High wing / large

Tprop nacelle

configuration

Advanced

Integration of

syst. in nacelle

Rotor-less tail for

Fast Rotorcraft

WP A-0.2 WP A-1.2 WP A-2.2 WP A-3.2 WP A-4.2 WP A-5.2 WP B-0.2 WP B-1.2 WP B-2.2 WP B-3.2 WP B-4.2

Business Aviation

OAD & config.

Mgt

CROR & UHBR

configurations

NLF smart

integrated wing

Tailored front

fuselage

Active load

control

Office Centered

Cabin

SAT

OAD &

configuration Mgt

More affordable

composite

structures


Pressurized

fuselage for Fast

RotorcraftWP A-0.3 WP A-1.3 WP A-2.3 WP A-3.3 WP B-0.3 WP B-1.3 WP B-3.3 WP B-4.3

LPA

OAD & config.

Mgt

Novel high

performance

configuration

Extended

laminarity

Innovative shapes

& structure

RotorCraft OAD &

configuration Mgt

More efficient

wings

technologies

Highly integrated

cockpit

More affordable

composite

fuselage

WP A-0.4 WP A-1.4 WP A-3.4 WP B-0.4 WP B-1.4 WP B-3.4 WP B-4.4

Eco-Design TA

Link

Novel certification

processes

Eco-Design for

airframe

Regional a/c

OAD & config.

Mgt

Flow & shape

control

More affordable

small a/c

manufacturing

Low weight, low

cost cabin

WP B-0.5 WP B-3.5

Eco-Design TA

Link

Advanced

integration of


New materials &

manufacturing


EfficiencyB - High Versatility and Cost Efficiency

75

CPW02 : AIRFRAME ITD ST List

• 4 Strategic Topics (ST)

• Total funding of 15,5 M€

Activity Line

Identification Title Leading

Company Funding

(M€)

A AIR-01-04 Next generation high load movables for high speed aircrafts

AIB, DAv, SAAB

5

B AIR-02-09 Design, manufacturing of mock-up and manufacturing of flight worthy prototype of high visibility, crashworthy, low-drag integrated cockpit section for a civil tiltrotor

AW 3,5

B AIR-02-10 Design, manufacturing of mock-up and manufacturing of flight worthy prototype of non-conventional pressurized centre section for a civil tiltrotor fuselage.

AW 3,5

B AIR-02-11 Design, manufacturing of mock-up and manufacturing of flight worthy prototype of light weight, monolythic, integrally stiffened, post buckled composite rear fuselage section and empennage for a civil tiltrotor fuselage.

AW 3,5

TS A-0:

Management &

Interface

TS A-1:

Innovative

Aircraft

Architecture

TS A-2:

Advanced

Laminarity

TS A-3: High

Speed Airframe

TS A-4: Novel

Control

TS A-5: Novel

travel

experience


Overall

Management

Optimal engine

integration on

rear fuselage

Laminar nacelle

Multidisciplinary

wing for high &

low speed

Smart mobile

control surfaces

Ergonomic flexible

cabin


Business Aviation

OAD & config.

Mgt

CROR & UHBR

configurations

NLF smart

integrated wing

Tailored front

fuselage

Active load

control

Office Centered

Cabin

WP A-0.3 WP A-1.3 WP A-2.3 WP A-3.3

LPA

OAD & config.

Mgt

Novel high

efficiency

configuration

Extended

laminarity

Innovative shapes

& structure

WP A-0.4 WP A-1.4 WP A-3.4

Eco-Design TA

Link

Novel certification

processes

Eco-Design for

airframe


Efficiency

HPE Related WPs

76

AIR-01-04 Next generation high load movables for high speed aircrafts

Note: a coloured square means a contribution of the ST to the WP

AIR-01-04: Next generation high load movables for high speed aircrafts (1/3) OVERVIEW

77

• Leading Companies: Airbus, Dassault Aviation, SAAB

• Indicative Funding Value: 5 M€

• Duration: 84 months

• Indicative Start date: Q4/2016 • Overview:

– To design and demonstrate multifunctionnal control surfaces for next generation aircrafts, and also associated design, manufacturing, testing and certification processes

– New control surfaces will have the objective of:

• Adapting the geometry to the flight point (morphing)

• Reducing loads (more efficient loads alleviation)

• Reducing weight through optimized structures

• Reducing noise

• Reducing manufacturing costs (thermoplastics, 3D printing, ...)

– Improvements of validation and certification methods will address the integration of simulation as an accepted contribution to the means of compliance

AIR-01-04: Next generation high load movables for high speed aircrafts (2/3) SCOPE of WORK and SCHEDULE

78

• Explore one or more innovative movable solutions – E.g.:

– Multifunctional slat for a turbulent wing, non-recurring cost and kinematics interface focused

– Adaptive winglet: active winglet trailing edge for large winglet concepts, active winglet leading edge

– ...

• Assess feasibility and impact on aircraft performances of the proposed solutions:

– Preliminary load assessment, mechanical and functional definition, leading to a weight estimate

– Estimation of benefit in terms of drag, noise, load control, etc.

– Preliminary analysis of integration solutions and of impact of system failures

• Select a set of proposed target applications and solutions for development to TRL= 4 to 5

• Develop and test the selected solutions

– Full scale prototype of the movable or critical part to be designed, manufactured and tested

– Critical aero, loads and/or noise performances demonstration through WTT or in flight S1 S2 S3 S4 S5 S6 S7 S8 S9 S10 S11 S12 S13 S14

Capture of specifications

Exploration and assesment of solution 1

…

Exploration and assesment of solution n

Synthesis of assesments, iterations with

Airframers

Selection of concepts for developpement

Developpement of selected solution A Test

Developpement of selected solution B Test

…

Process developpement plan finalisation

Developpement of process a Appl ic. to conc. A and/or B

Developpement of process b Appl ic. to conc. A and/or B

….

Synthesis

Dev. and valid.

Dev. and valid.

PDR CDR Manufacturing

PDR CDR Manufacturing

79

Demonstrated capabilities on: • Aerodynamic design, Loads assessment, Structural design, Acoustic

design with experience of qualification and certification,

• Aerodynamic, loads and structural testing, including support to

certification,

• Configuration performance assessment,

• Innovative Manufacturing and associated cost assessment,

• Flow control technologies for application at airframe components.

In addition the applicant shall have: • R&T background in design, testing and demonstration of flow control

techniques in WTT facilities.

• Integration of sensors and flow control actuators in WTT

• Laboratory testing facilities for flow control actuator testing

• Expertise to design, build and test deployable vortex generators

• Tools and expertise to design and test morphing components

AIR-01-04: Next generation high load movables for high speed aircrafts (3/3) SKILLS

TS B-0:

Management &

Interface

TS B-1: Next

Generation

optimized wing

box

TS B-2:

Optimized high

lift

configurations

TS B-3:

Advanced

Integrated

Structures

TS B-4:

Advanced

Fuselage


Overall

Management

Wing for

incremental lift &

transmission shaft

integration

High wing / large

Tprop nacelle

configuration

Advanced

Integration of

syst. in nacelle

Rotor-less tail for

Fast Rotorcraft


SAT

OAD &

configuration Mgt

More affordable

composite

structures


Pressurized

fuselage for Fast


RotorCraft OAD &

configuration Mgt

More efficient

wings

technologies

Highly integrated

cockpit

More affordable

composite

fuselage

WP B-0.4 WP B-1.4 WP B-3.4 WP B-4.4

Regional a/c

OAD & config.

Mgt

Flow & shape

control

More affordable

small a/c

manufacturing

Affordable low

weight, human


Eco-Design

Managt & MPR

technologies

Advanced

integration of


New materials &

manufacturing


HVC Related WPs

80

AIR-02-09 Design, manufacturing of mock-up and manufacturing of flight worthy prototype of high visibility, crashworthy, low-drag integrated cockpit section for a civil tiltrotor

AIR-02-10 Design, manufacturing of mock-up and manufacturing of flight worthy prototype of non-conventional pressurized centre section for a civil tiltrotor fuselage.

AIR-02-11 Design, manufacturing of mock-up and manufacturing of flight worthy prototype of light weight, monolythic, integrally stiffened, post buckled composite rear fuselage section and empennage for a civil tiltrotor fuselage.

AIR-02-09: Design, manufacturing of mock-up and manufacturing of flight worthy prototype of high visibility, crashworthy, low-drag integrated cockpit section for a civil tiltrotor (1/3)

OVERVIEW

81

• Leading Companies: AW

• Indicative Funding Value: 3.5 M€

• Duration: 68 months


– Design, analyze, manufacture, test and deliver Technology Demonstrator of high visibility, crashworthy, low-drag integrated cockpit section for Next Generation Civil TiltRotor (NGCTR)

– NGCTR cockpit comprises radome, pressurized crew compartment with seating provisions, instrument panel, avionics bays, nose landing gear bay, pressurized bulkhead, transparencies, provisions for crew emergency egress

– The fuselage cockpit section design has to satisfy a specified certification basis (selection of CS25, CS29 requirements with additional ones for the tiltrotor). The selected partner shall provide appropriate documentation to substantiate compliance to the applicable requirements in order to achieve a “Permit to Fly”

metallic, hybrid (metallic and composite), …


SCOPE of WORK and SCHEDULE

82

The scope of work of the present Call for Core Partner(s) is:

• To design and substantiate the cockpit section of the production aircraft to Preliminary Design Review (PDR) maturity level

• Starting from the cockpit section of the production aircraft (PDR maturity level) to design, analyze, manufacture, test, supply and support through integration, test and flight, a derivative cockpit section for the fuselage of the Technology Demonstrator of NGCTR according to the requirements, specifications and directives supplied by AgustaWestland (AW).

Core Partner(s) shall:

• To supply all documentation required to achieve the “Permit to Fly” of the Technology Demonstrator

• To propose and investigate innovative solutions to reach NGCTR requirements (weight, interfaces, manufacturing, ...)

• To suggest and evaluate the integration of advanced design and manufacturing solutions

NGCTR Cockpit development schedule is: Ref. No. Title - Description Type* Due Date [T0 + months]

D1 Minutes of Cockpit System Requirement Review R T0+1

D2 Minutes of Cockpit PDR for Production Design R T0+8

D3 Minutes of Demonstrator Cockpit SRR R T0+10

D4 Minutes of Demonstrator Cockpit PDR R T0+17

D5 Minutes of Demonstrator Cockpit Test Plan Review R T0+20

D6 Minutes of Demonstrator Cockpit CDR R T0+24

D7 Demonstrator Cockpit Design R T0+26

D8 Minutes of Demonstrator Cockpit TRR R T0+37

D9 Demonstrator Module Qualification Reports R T0+52

D10 Minutes of Flight Activities R T0+68

M1 Demonstrator Cockpit Test Articles Available to AW D T0+39

M2 Demonstrator Cockpit Hardware Available to AW D T0+49

*Type: R: Report, RM: Review Meeting, D: Delivery of hardware/software


SKILLS

83

Suitable Core Partner(s) across the proposed team shall:

• Have as a minimum a proven track record of design, analysis, construction and management of significant aircraft structural modules or components in metallic and composite according to recognized industrial quality standards

• Use the design, analysis and configuration management tools of the aeronautical industry

• Experience with TRL Reviews or equivalent technology readiness assessment techniques in research and manufacturing projects in the aeronautical industry

• Be capable of designing and manufacturing/procuring all tooling and assembly jigs as required

• Be capable to manufacture, test, checks NGCTR components to assure the required production quality

• Have the capacity to support the production of documentation and means of compliance to achieve experimental prototype “Permit to Fly” with the appropriate Airworthiness Authorities

Core Partner(s) should:

• Have experience of collaborating with industrial partners, institutions, technology centres, universities and OEMs (Original Equipment Manufacturers) within international R&T projects

• Have a Quality System approved to international standards (i.e. EN 9100:2009/ ISO 9001:2008/ ISO 14001:2004)

• Be capable of supporting the overall aircraft configuration management

• Be capable of performing Life Cycle Analysis (LCA) and Life Cycle Cost Analysis (LCCA) of materials and structures

AIR-02-10: Design, manufacturing of mock-up and manufacturing of flight worthy prototype of non-conventional pressurized centre section for a civil tiltrotor fuselage (1/3)

OVERVIEW

01/12/2015 84



• Duration: 68 Months


– Design, analyze, manufacture, test and deliver Technology Demonstrator of high visibility, crashworthy, low-drag integrated pressurized cabin section for next generation civil tiltrotor (NGCTR).

– Cabin comprises pressurized passenger compartment with seating provisions, passenger door, transparencies, main landing gear bays, provisions for systems, cargo, passenger emergency egress, pressurized bulkhead

– The fuselage cabin section design has to satisfy a specified certification basis (selection of CS25, CS29 requirements with additional ones for the tiltrotor). The selected partner shall provide appropriate documentation to substantiate compliance to the applicable requirements in order to achieve a “Permit to Fly”

metallic, composite,...



85


• To design and substantiate the cabin section of the production aircraft to Preliminary Design Review (PDR) maturity level

• Starting from the cabin section of the production aircraft (PDR maturity level) to design, analyze, manufacture, test, supply and support through integration, test and flight, a derivative cabin section for the fuselage of the Technology Demonstrator of NGCTR according to the requirements, specifications and directives supplied by AgustaWestland (AW).





NGCTR Cabin development schedule is: Ref. No. Title - Description Type* Due Date [T0 + months]

D1 Minutes of Cabin System Requirement Review R T0+1

D2 Minutes of Cabin PDR for Production Design R T0+8

D3 Minutes of Demonstrator Cabin SRR R T0+10

D4 Minutes of Demonstrator Cabin PDR R T0+17

D5 Minutes of Demonstrator Cabin Test Plan Review R T0+20

D6 Minutes of Demonstrator Cabin CDR R T0+24

D7 Demonstrator Cabin Design R T0+26

D8 Minutes of Demonstrator Cabin TRR R T0+37



M1 Demonstrator Cabin Test Articles Available to AW D T0+39

M2 Demonstrator Cabin Hardware Available to AW D T0+49



SKILLS

86













AIR-02-11: Design, manufacturing of mock-up and manufacturing of flight worthy prototype of light weight, monolithic, integrally stiffened, post buckled composite rear fuselage section and empennage for a civil tiltrotor fuselage (1/3)

OVERVIEW

01/12/2015 87



• Duration: 68 Months


– Design, analyze, manufacture, test and deliver Technology Demonstrator of high visibility, crashworthy, low-drag integrated Rear Fuselage and Tail sections for next generation civil tiltrotor (NGCTR).

– The Rear Fuselage section comprises cargo/baggage compartment and door, provisions for systems. The Tail section comprises fixed and control surfaces with the supports for the actuator systems.

– The Rear Fuselage and Tail section design has to satisfy a specified certification basis (selection of CS25, CS29 requirements with additional ones for the tiltrotor). The selected partner shall provide appropriate documentation to substantiate compliance to the applicable requirements in order to achieve a “Permit to Fly”

thermoplastic, composite, …



88


• To design and substantiate the rear fuselage and tail section of the production aircraft to Preliminary Design Review (PDR) maturity level

• Starting from the rear fuselage and tail section of the production aircraft (PDR maturity level) to design, analyze, manufacture, test, supply and support through integration, test and flight, a derivative rear fuselage and tail section for the fuselage of the Technology Demonstrator of NGCTR according to the requirements, specifications and directives supplied by AgustaWestland (AW).





NGCTR Rear Fuselage and Tail development schedule is: Ref. No. Title - Description Type* Due Date [T0 + months]

D1 Minutes of Rear Fuselage and Tail System Requirement Review R T0+1

D2 Minutes of Rear Fuselage and Tail PDR for Production Design R T0+8

D3 Minutes of Demonstrator Rear Fuselage and Tail SRR R T0+10

D4 Minutes of Demonstrator Rear Fuselage and Tail PDR R T0+17

D5 Minutes of Demonstrator Rear Fuselage and Tail Test Plan Review R T0+20

D6 Minutes of Demonstrator Rear Fuselage and Tail CDR R T0+24

D7 Demonstrator Rear Fuselage and Tail Design R T0+26

D8 Minutes of Demonstrator Rear Fuselage and Tail TRR R T0+37



M1 Demonstrator Rear Fuselage and Tail Test Articles Available to AW D T0+39

M2 Demonstrator Rear Fuselage and Tail Hardware Available to AW D T0+49



SKILLS

89













innovation takes off - clean skycleansky.eu/sites/default/files/documents/4- cs2cpw03id - overview...

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