innovation takes off - clean sky · • shape, component design and structural analysis using catia...

Innovation Takes Off


Clean Sky 2 Information Day dedicated to the

9th Call for Proposal (CfP09)

Topics related to FAST ROTORCRAFT IADP

Clean Sky 2 / FRC – General Session

FRC Overview

Filling the Mobility Gap

TRANSPORT RANGE & PRODUCTIVITY

Unprepared Area Helideck

Door-to-Door

Large Airport

Regional Airport

Heliport Local airfield

Local Transport Short range Medium Range Long Range

Helicopter

Compound R/C

Tilt-Rotor A/C

Turboprop

Turbofan & CROR

EMS, SAR, Coast guard

Disaster relief Oil & Gas offshore

Corporate Transport Air Taxi

MISSIONS AIRFIELD

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Clean Sky 2 / FRC – General Session

FRC Overview

Clean Sky 2 Context

Leonardo

Fast Rotorcraft

Leonardo Helicopters Airbus HElicopters

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Unique capabilities:

Hover/Vertical flight: as good as helicopter

Cruise speed exceeding 220 kt (410 km/h)

LifeRCraft (1) - The Compound Rotorcraft A new game–changing rotorcraft

NB: images may not reflect CS2 demonstrator sizing & components (for illustration purpose only)

(1) LifeRCraft = Low Impact, Fast & Efficient RotorCraft (2) VTOL: Vertical Take-Off & Landing

Enabling to meet expectations for citizens’ health & safety, door-to-door mobility, environment protection:

Shorter time for Rescue & Emergency, Air Taxi

Acoustic footprint & CO2 emission lower than helicopter (3)

Eco-friendly materials, greener life cycle Continue with LifeRCraft

To prepare a competitive product

Weight, weight, and weight…

Additional components: wing and lateral rotors

Strong engines & power train

Aerodynamic efficiency: Also crucial!

Cruise: low drag, high Lift-to-Drag ratio

Hover/ vertical flight: efficiency & manoeuvrability

Cost efficiency: Must outperform helicopter

Operating cost (per kg payload/km)

Recurring cost NO MORE TOPICS WILL BE LAUNCHED…..

FRC Overview NextGenCTR Objectives and Challenges

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ENVIRONMENTAL: CO2 and Noise Footprint reduction IND. LEADERSHIP: Reduced cost of ownership (Ops. & MRO) EU MOBILITY: Fast Forward Speed MIX OF ABOVE 3: High Efficiency, High Productivity

4. Optimized Tail

configuration

3. Advanced Wing

architecture

1 .Fixed-engine, Split gearbox

drivetrain concept

5. Advanced Modular,

Distributed & Scalable FCS

2. Efficient nacelle

architecture

NGCTR – Company objectives aligned with CS2

Key objectives will be pursued within CS2 by a Technology Demonstrator focusing on the Design & Development effort of Key Enabling Technologies:

1. Fixed-engine, Split Gearbox Drivetrain concept 2. Efficient Nacelle architecture 3. Advanced Wing architecture 4. Optimized Tail configuration 5. Advanced Modular, Distributed & Scalable Flight Control System

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New Technologies to be tested within CS2 for First Flight (TRL =6)

FRC IADP NGCTR-TD Objectives

New Wing (no dihedral and no swept) Integration (T-WING)

Mast tilt for control improvement (LH)

Splitted gearbox architecture to support non tilting engine (LH)

Advanced empennage configuration (LIFTT)

Innovative fuel system (DigiFuel & DEFENDER)

Distributed FCS system (LH)

New control laws (LH)

Flow through engine

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New Technologies to be tested within CS2 after First Flight (TRL =<6)

FRC IADP NGCTR-TD Objectives

Rotor system new material application (MMC,...)

(LH)

General System new applications (i.e. Electrical low pressure

compressor, ...) (Call to be assigned)

Additive Manufacturing technology gearbox housing –

(AMATHO)

New tailcone & empennage material manufacturing (LIFTT)

Active inceptors (Partner to be engaged)

SYSTEM ITD - Proprietary to one or more members

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JTI-CS2-2018-CFP09-FRC-01-25 Smart Active Inceptors System definition for Tilt Rotor application

RIA 1.25 Leonardo Helicopters

JTI-CS2-2018-CFP09-FRC-01-26

Design, manufacture and deliver a high performance, low cost, low weight Nacelle Structure for Next Generation TiltRotor (NGCTR) - Technology Demonstrator (TD)

IA 5.20 Leonardo Helicopters

JTI-CS2-2018-CFP09-FRC-01-27

Tilt Rotor Whirl Flutter experimental investigation and assessment

RIA 5.00 Leonardo Helicopters

JTI-CS2-2018-CFP09-FRC: 3 topics 11.45

FRC IADP CfP 09 list of topics

JTI-CS2-2018-CFP09-FRC-01-25

Smart Active Inceptors System definition

for Tilt Rotor application – 1.25 Me

Duration: 18 months

Type of Action: RIA

Innovation Takes Off http://www.cleansky.eu/content/homepage/about-clean-sky-2

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JTI-CS2-2018-CFP09-FRC-01-25

Active inceptors (Partner to be engaged)

Tiltrotor control presents specific peculiarities which make traditional inceptors not fully applicable in all tiltrotor flights phase. Hence, a research activity to define the most effective inceptors configuration for tiltrotor application must be implemented.

Goal/Scope of work

To design, develop, and manufacture the cockpit inceptors system needed to translate the NGCTR pilots’ basic inputs (pilot and co-pilot) into suitable digital commands to the aircraft Fly-By-Wire Flight Control System, whilst providing adequate cues to the crew.

The main objective is to make piloting of Tilt Rotor more intuitive and effective; The design has to focus on inceptors’ mechanical interface and ergonomics so that FCS augmentation can be further improved. Moreover, increased situational awareness allowed by active inceptors can be made more specific by tailoring dedicated functionalities to Tilt Rotor application.

The Inceptors System shall allow aircraft control by translating the pilots’ and co-pilot’s basic inputs into suitable digital commands to the aircraft FCS, by means of

• pilot’s and co-pilot’s right-hand active inceptors • pilot’s and co-pilot’s left-hand active inceptors • pilot’s and co-pilot’s pedals • Pedals are intended as inceptors, as per SAE ARP 5764.

Different ergonomics architecture shall be considered, for instance Side-stick short pole inceptor. Rotary inceptor Linear inceptor A combination of the above Any configuration conceived by the Applicant.

JTI-CS2-2018-CFP09-FRC-01-25

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1. Identification Operational Scenarios and Requirement Analysis.

Identification of potential solutions. Different ergonomics architecture shall be considered, for instance side-stick short pole, rotary, linear, a combination of previous configuration, any configuration conceived by the Applicant. The number of degrees of freedom is part of the study.

2. Evaluation Scoring of identified solutions (for instance leveraging on analysis, simulation, similar or

equivalent units already implemented, 3D-printed prototypes).

3. Simulator / Test-Bench Validation Production of a maximum of three system lab prototypes, selected by Topic Leader from

solutions identified in previous steps. (each system prototype includes left- and right- hand inceptor and pedals, for single pilot simulation).

System validation by means of pilot-in-the-loop simulation at WAL premises.

4. Specification definition Results from test bench validation shall be used by Topic Leader to select final

configuration.

Issue of a Specification for the selected configuration.

JTI-CS2-2018-CFP09-FRC-01-25

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Schedule

Title - Description Type Due Date Concept Exploration & Definition

R t0 + 3 months

Evaluation Prototypes HW t0 + 5 months Test Bench Prototypes HW t0 + 12 months Inceptors Specification R t0 + 18 months

JTI-CS2-2018-CFP09-FRC-01-25

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Special skills, Capabilities expected from the Applicant(s)

Experience in research, development and manufacturing (or integration) in the following technology fields: • Cockpit flight controls, with particular emphasis on active stick design as per SAE-ARP-5764

guidelines. • High performance DC brushless servomotors and drive systems, • Compact and reliable sensors and switches. • High integrity control electronics. • Grip ergonomic design and optimisation.

Experience of aeronautic rules, certification processes and quality requirements. Experience in design and validation of airborne equipment, either cockpit flight control systems, avionics systems (embedding complex HW and DAL-A SW) or both. Capacity to design complex electronic HW and experience in performing EMC analyses and experimental assessments. Design Organization Approval (DOA) desirable. Shape, component design and structural analysis using CATIA v5 and NASTRAN, or compatible SW tools.

CS2 Info Day CfP08

JTI-CS2-2018-CFP09-FRC-01-26

JTI-CS2-2018-CFP09-FRC-01-26

Design, manufacture and deliver a high

performance, low cost, low weight Nacelle

Structure for Next Generation TiltRotor (NGCTR)

- Technology Demonstrator – 5.1 Me

Duration: 40 months

Type of Action: RIA


JTI-CS2-2018-CFP09-FRC-01-26

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Nacelle and Flow through engine

The Partner shall work with the IADP Leader and the Core partner responsible for the wing to develop the NGCTR TD Nacelle Structure to be installed on the NGCTR TD for flight test. The selected Partner shall be responsible for:

• Detail design and manufacture of the nacelle tilting structural elements.

• Detail design and manufacture of the nacelle fixed structural elements interfacing with the tilting ones including the interface mechanism(e.g the cowling / fairing support)

• Detail design and manufacture of the nacelle engine bay structural elements( e.g firewalls, seals, ducts, engine mounts, thermal blankets and engine bay floor.

• Develop and execute plans for design, analysis, manufacture and test as necessary for the elements (fire test; birdstrike; structural element; endurance of tiliting fairing mechanism; any other tests required) in order to support to LHD for the production of the relevant documentation to achieve a permit to fly for the TD.

JTI-CS2-2018-CFP09-FRC-01-26

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JTI-CS2-2018-CFP09-FRC-01-26

Ref. No. Main Steps Type Due Date

1 Kick-off meeting minutes (KOM) R T0

4 NGCTR TD Nacelle Design Data Set and final Interface Definition Documents

R T0+15

5 First Article Inspection Report R T0+24

7 Delivery of LH and RH Nacelles for flying aircraft H T0+28

9 NGCTR TD Test Readiness Review (TRR) R T0+40

Schedule

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Special skills, Capabilities expected from the Applicant(s) • Have as a minimum a proven track record of the construction of significant aircraft structural modules

or components

• Be experienced in the design and manufacturing of structures in non-conventional and conventional composite materials (thermoset and thermoplastic plus high temperature systems) and innovative and conventional metallic components

• Have the capability to manufacture and assemble composite and metallic parts

• Shape, component design and structural analysis using CATIA v5 and NASTRAN, or compatible SW tools.

• Proven experience of collaboration with other aeronautical companies in industrial air vehicle developments

• 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.

• Be capable of specifying and conducting material, structural and endurance tests including full scale.

• Have qualification competences: design organization approval (DOA) is desirable but not mandatory.

• Have access to the qualification process to obtain the “Permit to Fly” of the NGCTR.

JTI-CS2-2018-CFP09-FRC-01-26

JTI-CS2-2018-CFP09-FRC-01-27

Tilt Rotor Whirl Flutter experimental investigation

and assessment – 5.0 Me

Duration: 54 Months

Type of Action: RIA


New Technologies to be tested within CS2 after First Flight (TRL =<6)

JTI-CS2-2018-CFP09-FRC-01-27

To design, manufacture, test and post-process the test data of a semi-span aero-elastic tiltrotor powered model in a wind tunnel test facility.

To obtain experimental data necessary to validate the methodologies, tools and design envelope as pertains the Whirl Flutter phenomenon on aircraft configurations suitable for the NGCTR.

1. Preliminary assessment and Model Design To cover all aspects pertaining to the construction of an aeroelastically scaled model suitable

to fit the ITD leader requirements

To determine model strength and stability margins to ensure safe operation in the selected wind tunnel

2. Aeroelastic Model Detailed Design To design of the aeroelastic wind tunnel model: support system, wing, pylon/nacelle, drive

system, power unit, prop-rotor, excitation systems, slip-ring, fairings

To determine the rotor blade and wing aerofoil aerodynamic characteristics at the Reynolds number expected in the wind tunnel

3. Manufacturing, assembly To provide proper instrumentation to measure loads, accelerations, movements on rotor,

pylon and wing subsystems

4. Model Preparation and Wind tunnel testing Functional Test, rotor tracking and balancing, model dynamics characterization

Accomplishment of wind tunnel test on three different configurations of the model (mass and stiffness changes)

5. Wind tunnel data analysis and post-processing Analytical results validation to achieve the necessary correlation level

JTI-CS2-2018-CFP09-FRC-01-27

Ref. No. Main Steps Type Due Date

1 Kick-off meeting RM T0

5 Model PDR (go ahead with detailed design) RM T0+17

7 Model CDR (go ahead with manufacturing) RM T0+29

9 Wind Tunnel Entry D T0+46

JTI-CS2-2018-CFP09-FRC-01-27

Schedule

Expected capabilities from the Applicant

Proven skills in rotorcraft dynamics , aerodynamics and aeromechanics

Wind tunnel powered model design, manufacturing, instrumentation, piloting

Wind tunnel tests management, test conduction and experimental data analysis

Qualified and demonstrated skills in analytical modelling and results validation

JTI-CS2-2018-CFP09-FRC-01-27

Any questions?

[email protected]*


Last deadline to submit your questions: 5th December 2018, 17:00 (Brussels time)

*Note: email address only active as from 23/10/2018 (Official Call Opening date via the Participant Portal)

mailto:[email protected]









Thank You

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.

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