Innovation Takes Off Clean Sky 2 Information Day dedicated to the 3rd Call for Proposal (CfP03)

Fast Rotorcraft / Airframe Next Generation Civil – NGCTR

Brussels, 17 March 2016

Innovation Takes Off Global Competition and Demanding Market

Markets Require more: Speed, range, capacity, productivity, efficiency and sustainability… Setting new standards

Fast Rotorcraft IADP

AgustaWestland Airbus Helicopters NextGenCTR LifeRcraft Tiltrotor Compound

Images for illustration purposes only Setup and Implementation From Clean Sky towards Clean Sky 2 NGCTR Work Breakdown Structure

Not legally binding – AW Confidential Overview of NGCTR topics in CfP03

Type of Funding JU Topic ID No. Title action (k€) Development and demonstration of a high power JTI-CS2-2015-CFP03-FRC-01-02 IA 750 density homokinetic drive joint for civil rotor applications Next generation smart active JTI-CS2-2015-CFP03-FRC-01-08 IA 1500 inceptors for a civil tiltrotor Next Generation Fuel Storage JTI-CS2-2015-CFP03-FRC-01-10 IA 1000 System High Speed HVDC JTI-CS2-2015-CFP03-FRC-01-12 IA 1000 Generator/Motor Electrical Power Distribution JTI-CS2-2015-CfP03-FRC-01-13 IA 1500 System for Tiltrotor

Development and demonstration of materials and manufacturing process for JTI-CS2-2015-CFP03-AIR-02-02-52 IA 500 high structural damping composite beams for civil rotor and airframe applications JTI-CS2-2015-CFP03-FRC-01-02: Homokinetic Joint for rotor hub

• Indicative Funding Value, Duration: 0.75 Mk€; 48 Months. • Type of Action: IA • Basic Design Requirements:  Transmit 5000 hp continuous , 10000 hp transient  At 450-500 rpm  Through 11-degree misalignment angle  Within about 350 mm diameter, around 170 mm diameter shaft (mast)  Integrate with proprotor hub structure as necessary to minimize size, weight, and kinematic errors.

• Key Objective:  Flight-cleared units for full-scale demonstrator aircraft

• Technological Challenges:  Small size relative to power transmission or “high power density”  Unique configuration unaffected by external patents  Low operating cost and EASA CS-29 damage tolerance capability JTI-CS2-2015-CFP03-FRC-01-08: Next generation smart active inceptors for a civil tiltrotor (1/2)

• Indicative Funding Value: 1.5 M€ • Duration: 48 months up to first flight, then up to 66 months for flight trials support • Type of Action: IA • Main Objective:  design, development, manufacture and qualification of smart fly-by-wire active inceptors for the future generation cockpit of a civil tiltrotor. The designed units will be subjected to test pilots’ functional and ergonomic assessments, qualified for experimental flight clearance and integrated in the TiltRotor flying demonstrator.  NGCTR inceptors system will be part of a complex Fly By Wire distributed Flight Control System JTI-CS2-2015-CFP03-FRC-01-08: Next generation smart active inceptors for a civil tiltrotor (2/2)

• Inceptors Configuration  Distributed Inceptor Control Units (ICUs) will enable the necessary basic and enhanced (smart) inceptors’ functions  throttle / power lever for power control  ergonomic trade-off analysis required to implement best solution suitable for different TiltRotor modes of operation (e.g., hover/conversion/airplane)  side-arm inceptor for pitch/roll control  center-trim pedals for directional control JTI-CS2-2015-CFP03-FRC-01-10: Fuel Storage System

• Indicative Funding Value, Duration: 1 M€; 48 Months. • Type of Action: IA. • Main Objective:  to support the leader during design phase of a fuel storage system that: 1. minimize the explosive atmosphere inside the tanks 2. ease the installation of the tanks 3. minimize fuel bladder weight 4. integrate gauging capability

NOTE: the storage system design implies a filler foam design that maintain the tank shape after installation

• Overview:  Minimization of explosive atmosphere; Fuel bladder capable to segregate (e.g. with an internal diaphragm) the fuel part from the vented part (e.g. like a hydraulic diaphragm accumulator)  Ease the installation of the tanks; smart interconnection with quick connect-disconnect device  Minimize fuel bladder weight; Divide the storage function (internal liner) from the mechanical resistance function (external fabric), adding this only where required Using closed cell foam technology to mechanically protect and reinforce locally the bladder structure  Integrate a gauging capability; Capacitive gauge/strain gauge/piezo sensor could be built using embedded, dedicated layer into the tank. JTI-CS2-2015-CFP03-FRC-01-12: High Speed HVDC Generator/Motor

APU GEN • Indicative Funding Value, Duration: 1 M€; 66 Months. ENGINE 1 ENGINE 2 • Type of Action: IA. SG 1 GEN 1 GEN 2 SG 2

• Main Objective: EXT PWR HVDC DISTRIBUTION SYSTEM  Design, development, testing and flight qualification of a high speed / high voltage direct current (HVDC) generator system with an integral motor function to be installed onto the Next Generation HVDC LOADS HVDC LOADS

LVDC LVDC Civil Tilt Rotor DISTRIBUTION DISTRIBUTION

• Overview: LVDC LOADS LVDC LOADS  The 90kW generator will be mounted on the fixed engine gearboxes and/or the mid wing gearbox and will be driven at a speed proportional to proprotor speed (nominal speed 24000rpm).  The HVDC power from the generator (±270VDC) will be supplied to the electrical power distribution system for distribution to the respective loads, including flight safety critical loads.  Control of the generator will be ideally provided by an integral Generator Control Unit (GCU) or controller (dependant on generator technology), however a separate unit may be considered if suitable justification can be provided.  Cooling of the unit shall be via an integral cooling system with no direct use of the transmission cooling system.  As a secondary function, the generator shall also be able to act as a motor to drive various accessories through the aircraft gearbox, whilst on the ground. Nominal power 5kW.  Mathematical modeling and simulation tools shall be used to explore system concepts, operational behaviors, correct design errors, eliminate prototype steps and reduce the overall component and system test cycles.  The activities shall include design, manufacture and qualification, up to safety of flight,  to allow the system to be fitted to the prototype Tiltrotor NextGen CTR aircraft.

JTI-CS2-2015-CfP03-FRC-01-13: Power Distribution

APU GEN • Indicative Funding Value, Duration: 1.5M€; 66 Months. ENGINE 1 ENGINE 2 • Type of Action: IA. SG 1 GEN 1 GEN 2 SG 2

• Main Objective: EXT PWR HVDC DISTRIBUTION SYSTEM  Design, development, testing and flight qualification of high power Power Distribution Units (PDUs) for the safe control and protection of the High Voltage Direct Current (HVDC), Low Voltage Direct Current HVDC LOADS HVDC LOADS

(LVDC) electrical generation system supplies on the Next Generation LVDC LVDC Civil Tilt Rotor. DISTRIBUTION DISTRIBUTION

LVDC LOADS LVDC LOADS • Overview:  The HVDC distribution system provides control and protection of the HVDC supplies from the aircraft main power sources (two engine mounted integrated starter generators, two gearbox mounted generators, an APU generator and an external power source) to the applicable aircraft loads, including flight critical loads.  Significant consideration needs to be given to potential HVDC wiring faults that may be experienced and a robust protection mechanism implemented to minimise any damage these failures may cause.  The LVDC distribution system provides control and protection of the secondary distribution of LVDC to the applicable aircraft loads and incorporates the necessary power conversion from the primary HVDC supply to LVDC.  The primary power distribution architecture shall consider the use of Silicon Carbide technology whilst maintaining safety requirements for the overall system.  The equipment needs to incorporate extensive health monitoring, including PBIT, CBIT and IBIT that can be used to optimize maintenance actions and failure detection of not only itself but of the equipment connected to it.  Mathematical modeling and simulation tools shall be used to explore system concepts, operational behaviors, correct design errors, eliminate prototype steps and reduce the overall component and system test cycles.  The activities shall include design, manufacture and qualification, up to safety of flight, to allow the system to be fitted to the prototype Tiltrotor NextGen CTR aircraft. JTI-CS2-2015-CFP03-AIR-02-02-52: Development and demonstration of materials and manufacturing process for high structural damping composite beams for civil rotor and airframe applications

• Indicative Funding Value, Duration: 0.5M€; 54 Months. • Type of Action: IA. • Main Objective:  The objective of this project is flight-cleared composite beams with high structural damping integrated into the full-scale demonstrator aircraft.  The goal is to eliminate, or significantly reduce the requirement for discrete dampers by incorporating damping capability into the rotor head and airframe structure.  The rotor components are envisaged as “arms” of the rotor head that restrain the blades against centrifugal force, , and vertical motions while allowing lead-lag motions and providing the required damping (4%-5% ratio) of those motions.  The airframe structure components are envisaged to be elements of the wing and empennage used to control the dynamic response of the installation while maintaining the required static and fatigue strengths.

• Technological Challenges:  High fiber strains  Large deflections and fatigue strains in damping material(s)  Environmental effects (high-, and low-temperature moduli)  EASA CS-29 damage tolerance capability Clean Sky 2 Information Day dedicated to the 3rd Call for Proposals (CFP03) Brussels, 17th March 2016

FAST ROTORCRAFT IADP [LifeRCraft]

Innovation Takes Off FRC – Filling the Mobility Gap

MISSIONS AIRFIELD Helicopter Unprepared Area EMS, SAR, Helideck Coast guard Door-to-Door Disaster relief Oil & Gas offshore

Heliport Corporate Transport Local airfield Air Taxi

Turboprop Regional Airport & CROR Large Airport

Local Transport Short range Medium Range Long Range TRANSPORT RANGE & PRODUCTIVITY

3 FRC – Filling the Mobility Gap

MISSIONS AIRFIELD Helicopter Unprepared Area EMS, SAR, Helideck Coast guard Door-to-Door Disaster relief Compound Oil & Gas offshore R/C

Heliport Tilt-Rotor Corporate Transport Local airfield Air Taxi A/C

Turboprop Regional Airport Turbofan & CROR Large Airport

Local Transport Short range Medium Range Long Range TRANSPORT RANGE & PRODUCTIVITY

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

Not an airplane, better than a helicopter: a compound VTOL* architecture that retains the best of both aircraft types Unique capabilities:  Hover/Vertical flight: as good as helicopter  Cruise speed exceeding 220 kt (410 km/h) Flight experience started with X3 test bed Enabling to meet expectations for door-to-door mobility, environment protection, citizens’ health & safety:  Shorter time for Rescue & Emergency, Air Taxi  Acoustic footprint & CO2 emission lower than helicopter  Eco-friendly materials, greener life cycle Thanks to a comprehensive demonstration that will:  De-risk the integration of this new configuration thru the supply chain

 Pave the way for development & marketing prior non-EU Continue with LifeRCraft to prepare a competitors to secure market share of European rotorcraft competitive product industry.

(1) LifeRCraft= Low Impact, Fast & Efficient RotorCraft. 5 NB: images may not reflect CS2 demonstrator sizing & components (for illustration purpose only) (*) VTOL: Vertical Take-Off & Landing Example of benefit: Emergency Medical Service - Full Coverage within 1 hour

Required rescue bases: -7 to 8 bases with conventional H/C (main land only)

140 Kts

Range in 1 hour

6 Example of benefit: Emergency Medical Service - Full Coverage within 1 hour

Required rescue bases: -7 to 8 bases with conventional H/C (main land only) - 4 to 5 bases with compound R/C (land & islands)

140 Kts

Range in 1 hour

220Kts

7 LifeRCraft - The Compound Rotorcraft Major Challenges

Weight, weight, and weight… Even more crucial than for helicopters, why? 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

Unique opportunity to mature innovative technologies up to TRL 6 and showcase them for future compound and helicopter products

8 NB: images may not reflect actual demonstrator sizing & components (for illustration purpose only) CS2 LifeRCraft WorkLifeRCraft breakdown WBS

WP2.13: Validation, verification demonstration: WP2.1: Project management ground tests, flying demonstrator (AH) & integration activities (AH)

WP2.9: Actuators (AH) WP2.4: Lifting rotor (AH) WP7: Power plant: Engines - adaptation & installation (AH) WP2.5: Lateral rotors (AH) Tail boom & WP2.8: Electrical tail surfaces system: power (WP B-4.1) (AHE) generation, distribution & storage (AH - AHD) WP2.6: Mechanical drive: WP2.11: Cabin & Mission MGB, LGB, shafts (AH - AHP) Equipment (AH – AHD)

WP2.2: Airframe Structure (AHD) In ITD Airframe

Wing (WP B-1.1) (AHD) WP2.12: Flight control, WP numbers are referring to FRC project: AFCS, nav systems (AH) MGB: Main Gearbox WP2.3:Landing WP2.10: Avionics & LGB: Lateral Gearbox (AH) system (AH) Sensors

9 Topics for LifeRCraft Demonstration (WP2)

List of Topics proposed linked to WP2 Topics (LifeRCraft demo)

• FRC 02-09 Light weight, impact resistant, canopy for fast compound rotorcraft • FRC-02-11: Design and Realization of equipped engine compartments for a fast compound rotorcraft • FRC-02-15: Advanced Health Monitoring System for Next Generation Materials • FRC-02-16: Electrical Components

Postponed to next Call (CfP4)

10 FRC-02-09: Light weight, impact resistant, canopy for fast compound rotorcraft

• Leading Companies: Airbus Helicopters Deutschland • Indicative Funding Value, duration: 1.5 M€ ; 48 Months • Type of Action: IA

Overview: – Development and manufacturing of canopy structure for the LifeRCraft rotorcraft flying demonstrator – Features for installed equipment e.g. radar, FLIR, Cable cutter etc. Low aerodynamic drag – CS29 Compliant – Radar transparent nose – Cockpit doors and windshield – transparencies developped by other Partners – Interfaced with the main airframe section Dimensions are indicative and will be specified after partner selection developed by Core-Partner Romanian Cluster led by INCAS – Main challenges: light weight and bird strike resistance 11 FRC-02-11: Design and Realization of equipped engine compartments for a fast compound rotorcraft

• Leading Companies: Airbus Helicopters and Airbus Helicopters Deustchland • Indicative Funding Value, duration: 1,250 M€ ; 42 Months • Type of Action: IA

Overview: The aim of this Call for Proposals is to develop and manufacture the main elements constituting the engine compartments of the LifeRCraft demonstrator: upper cowlings, air intake, exhaust Ejector. The engine compartment module will be interfaced with the main airframe developed by Core-Partner in charge of the fuselage (Romanian Cluster, led by INCAS)

Dimensions are indicative and will be specified after partner selection 12 FRC-02-15: Advanced Health Monitoring System for next generation materials

• Leading Companies: Avio Aero • Indicative Funding Value, duration: 0,5 M€ ; 24 Months • Type of Action: IA

Overview: The aim of this Call for Partner is to define an advanced Health Monitoring System (HMS) for the Lateral Rotor GearBoxes and Engine to Main Gearbox reduction stages, developed for the Compound Rotorcraft Demonstrator in the frame of IADP FRC. The activities to be performed range from the identification of monitoring means and suitable sensing technologies, the development of the detection logic and algorithms, up to verification on test rigs and on gearbox module development test rig.

13 LifeRCraft - The Compound Rotorcraft Main tasks to be performed by the partner Packages for partnership Main activities for these packages include:  General design and interfaces according to the Airbus Helicopters specification (Plateau phase and common design offices with AH and/or the relevant Core partner will be planned)  Choice of technologies to be validated by Airbus Helicopters,  Detail design and component/subsystem development under full Partner’s responsibility, including the following activities: • Optimisation of Weight and Recurring cost, for FRC02-09 and 02-11 • Compliance with environmental requirements to be insured • Certification requirement have to be considered for design , but demonstration will be limited to flight clearance , for FRC02-09 and 02-11 • Manufacturing of parts and assembly of component/subsystem for integration demonstration (as specified for each topic ) • Lab tests (optional) & substantiations for flight clearance (as specified for each topic ) • Support to integration tests (ground and flight demonstration) for FRC02-09 and 02-11 • Analysis of tests results.

15 Questions ?

Any questions on the Call and topics can be addressed to the following mailbox: [email protected]

Deadline to submit your questions: 15th April 2016, 17:00

Not legally binding 16 Thank You

Not legally binding