FLIGHT-EMA (E-RUDDER)
Advanced Flight control system – Design Development and Manufacturing of an Electro Mechanical Actuator with associated Electronic Control Unit and Dedicated test Bench
| Coordinatore | COMPANIA ESPANOLA DE SISTEMAS AERONAUTICOS
Organization address
address: AVENIDA JOHN LENNON 4 contact info |
| Nazionalità Coordinatore | Spain [ES] |
| Totale costo | 1˙151˙041 € |
| EC contributo | 730˙613 € |
| Programma | FP7-JTI
Specific Programme "Cooperation": Joint Technology Initiatives |
| Code Call | SP1-JTI-CS-2012-01 |
| Funding Scheme | JTI-CS |
| Anno di inizio | 2013 |
| Periodo (anno-mese-giorno) | 2013-03-07 - 2015-12-06 |
Partecipanti
| # | ||||
|---|---|---|---|---|
| 1 |
COMPANIA ESPANOLA DE SISTEMAS AERONAUTICOS
Organization address
address: AVENIDA JOHN LENNON 4 contact info |
ES (MADRID (GETAFE)) | coordinator | 263˙584.50 |
| 2 |
FUNDACION TECNALIA RESEARCH & INNOVATION
Organization address
address: PARQUE TECNOLOGICO DE MIRAMON PASEO MIKELETEGI 2 contact info |
ES (DONOSTIA-SAN SEBASTIAN) | participant | 354˙637.00 |
| 3 |
MILITARTECNOLOGIE DIENST UND UBERWACHUNG SA
Organization address
address: "POLIGONO INDUSTRIAL AEROPOLIS, CALLE JUAN OLIVERT 24" contact info |
ES (SAN JOSE DE LA RINCONADA (SEVILLA)) | participant | 112˙392.00 |
Mappa
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Obiettivo del progetto (Objective)
'The FLIGHT-EMAFLIGHT-EMA project will design, develop, manufacture, tune and validate an innovative and smart Electro-Mechanical Flight Control system primary Actuator focused towards the study and validation of a future oil less Power by Wire aircraft. FLIGHT-EMA actuator will be based on a modular and efficient approach that will integrate easily exchangeable electric and mechanical components with sensors and control strategies that will allow automatic and autonomous safety control. The FLIGHT-EMA Electro-Mechanical Actuator will include its dedicated Electronic Control Unit, a Built In Test equipment to detect potential failures and a disable device to guarantee compatibility with emergency actuation. Different configurations will be studied and evaluated to determine the optimum system architecture from a technical point of view. Volume, mass, electrical consumption, power to mass ratio, reliability, durability and safety are concepts that will drive the development. The FLIGHT-EMA system will be tested and validated at several stages: Virtual validation at model level and finally actual experimental validations of the complete system through both on-ground and in-flight test campaigns. These sequential and complementary validations will assure thus a reliable, safe and efficient performance of the prototype and will provide data for a deep concept evaluation. For this validation purpose, the FLIGHT-EMA project will also design, manufacture and tune a Test Rig for FLIGHT-EMA Electro-Mechanical Actuator validation. FLIGHT-EMA Test Rig will allow installation both in Copper Bird® and in the ATR (Avions de Transport Regional) passenger cabin. The test bench will also include its own control system, inertia load simulation of the Rudder flight control surface involved weight and counter-load actuator with its hydraulic and electric power supply systems.'
Introduzione (Teaser)
For most of aeronautics history, moveable aircraft systems like landing gear and brakes have used hydraulic fluids to do their work. The new trend is towards all-electric aircraft, and rudder control is about to become the next beneficiary.