A European Project supported through the Seventh Framework Programmefor Research and Technological Development

CREAM ConsoRtiuM

ACknowlEdgEMEnt

CoMpACt And REliAblE ElECtRoniC intEgRAtEd in ACtuAtoRs And MotoRs

The CREAM project addresses the area of «Aeronautics and Air Transport» (ATT) started on the 1st of September 2009 and will last 36 months. The research lead in this project has received funding from the European Union Seventh Framework Programme (FP7/2007-2013) under grant agreement ACP8-GA-2009-243119 "CREAM".

www.creamproject.eu

Russia12. UAC

united kingdoms3. Semelab

France1. Sagem2. Hispano-Suiza14. Alma

switzerland5. EPFL6. Advanced Silicon7. LEM

Austria4. AIT

Hungary11. Naturen

greece10. TEIP13. Rotech Engineering

belgium8. Cissoid

germany9. Fraunhofer

project Coordinator : SAGEM Défense Sécurité, Paul Vassy,+33 1 58 11 35 81, paul.vassy@sagem.com

with the support of: ALMA Consulting Group SAS, Marie Letailleux, +33 1 41 49 12 65, mletailleux@almacg.com

ContACts

CREAM iMpACts

CREAM woRk plAn

CREAM project will help the European aeronautical industry to remain competitive in the challenging aeronautic market.

The technological outputs of CREAM project will lead to further economic impacts through its reliable EMA actuators in harsh thermal environments . It will impact our daily life by:

CREAM proposes an ambitious technological research program allowing to develop and validate a number of various emerging components, subsystems, packaging and motor technologies and to integrate them to a high performance smart electronic and motor technological platform destined to electric actuator preparation. The project is divided into 6 Work Packages (WP).

Aircraft Electro-Mechanical Actuators (EMA) : CREAM objectives compared with the state of the art (2008)

CREAM objECtivEsCREAM project objective is to reach new high performance and reliability capabilities of Electro-Mechanical Actuators (EMA) in harsh thermal environmental conditions ready to use in all-electric aircraft.

Provide high power density and compact •characteristics of electronics modules integrated in actuators or motors (reduction by a factor 2 of the electronic volume and mass).Provide advanced new concept of thermal •management of the electronic platform allowing higher performances and reliabilityProvide high temperature and compact • motor for actuators (reduction of 30% of the motor volume and mass)

Integrate the new • electronic and motor platform in actuator housing and a very severe thermal environment (above 200°C) providing efficient thermal management.Provide validation of • aeronautic reliability in high temperature at least at the same level than existing hydraulic systems (50.000 hours), and even better (100,000 hours) with health monitoring functionality.

wp0Management

wp1 Specifications and Trade-off

wp3 ActuatorGlobalIntegration

wp5 Standardisation,Exploitation andDissemination

wp4 Technological Platform Validation

wp2.1 Electronic Control Module Global Packaging

wp2.4 MCPM Reliability

wp2.2 Power Module

wp2.3 Electronic Control

wp2 MCpM

todAy’s CHAllEngEsthe current political, environmental and economical trends in the field of air transport are leading in the future towards the All Electric Aircraft (AEA). the goal of this concept is to eliminate as many hydraulic power sources and complicated circuit of high-pressure hydraulic lines as possible and provide power by wire (pwb) to supply electrical actuators.

Reliable electric actuators are one of the technical bottlenecks for realizing this ambitious technological vision of AEA. One of the real challenge for the implementing PWB actuation is the development of compact, reliable, electrically powered Electro-Mechanical Actuators (EMA) located in harsh thermal environment for most actuation applications (flight control actuators, braking system, landing gear actuators, propulsion inverters, various pumps, various auxiliary actuators).

CREAM technological research program

Future CREAM EMA technologyfuture aileron actuatorTarget weight/vol : 9 kg/4 l ,reliability > 50000h, Temp > 150°C

state of the art generation 2future aileron actuator (2009)Target weight/vol : 12,5 kg/6 l,reliability 40000h, Temp 85°Cunder development in Sagem

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2,0

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2004 2005 2006 2007 2008 2009 2010 2011 2012 2013

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1st gEnERAtion dRivEsAnd ContRol ModulE:- IGBT + Si Diodes- discrete technology- Thermal management- 80°C environment- 25000h reliability at 40°C- deported module- integration level < 1,5kw/kg

2d gEnERAtion dRivEs And ContRol ModulE:- IGBT + Si Diodes- Power integration 2-4kw/kg- Thermal management- 130°C environment- 50000h reliability- Deported or integrated module

3Rd gEnERAtion dRivEs And ContRol ModulE:- SiC JFET + Diodes- HT SOI control part- Power and control integration- Thermal management- HT capacitor- > 200°C environment- > 50000h MtbF (Obj 100000h)- Fully integrated in EMA- HVDC bus- Integration level 4 to 8 kw/kg

CREAM ConCEpt200°C 4 to 8 kw/kg [50000-100000h] reliability at 200°C 100000 power cycling of 100°C

kw/kg

tRlxF16 SVF (SABCA) 4,5Kw

2 3

A380 ETRAS (Hispano) 90°C 25Kw 135000 reliability at 25°C

6

AIPM Semikron (US) Automotive 42v 105°C 15Kw 30000 power cycling (100°C DT)

Arkansas APEI MCPM demonstrator (US)250°C 4Kw

9

High temp futur pump demonstrator (Sagem) 110°C 3Kw

8

Military launcher thrust vector control TAS f + Goodrich

1

787 EBAC(Boeing + Sagem)80°C 9Kw

4

Gulfstream flight control demo (GE) US 70°C 6Kw Controler not integrated

5

Future COVADIS flight control demonstrator (Airbus + Sagem) 85°C 4Kw, 40000h reliability

7

reduced operational cost for maintenance• (induced by higher performances and reliability), benefits of overall weight reduction, •

easier maintainability, •reducing operating costs (including reduced fuel burn) •enhanced safety.•