SIEDIT
Development of a Slat with Integrated Electrical Deicers for Icing Wind Tunnel Tests
| Coordinatore | GKN Aerospace Services Limited
Organization address
address: Ferry Road contact info |
| Nazionalità Coordinatore | United Kingdom [UK] |
| Totale costo | 370˙000 € |
| EC contributo | 185˙000 € |
| Programma | FP7-JTI
Specific Programme "Cooperation": Joint Technology Initiatives |
| Code Call | SP1-JTI-CS-2010-01 |
| Funding Scheme | JTI-CS |
| Anno di inizio | 2011 |
| Periodo (anno-mese-giorno) | 2011-01-03 - 2013-02-02 |
Partecipanti
| # | ||||
|---|---|---|---|---|
| 1 |
GKN Aerospace Services Limited
Organization address
address: Ferry Road contact info |
UK (East Cowes) | coordinator | 185˙000.00 |
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Obiettivo del progetto (Objective)
'There are presently two principle alternatives to engine bleed air Ice Protection on mid to large size aircraft; these are known as ‘electro-expulsive’ low power and ‘electro-thermal’ systems.
Whilst electro-thermal systems can perform very successfully when provided with adequate electrical power, an electro-expulsive system can be highly energy efficient and therefore extremely attractive on platforms where generator sizing is critical or less power is available for the ice protection system.
Neither system in isolation necessarily offers an ideal IPS solution for all future wing types. The purpose of this integration study is therefore not only to investigate the integration of the IPS technologies to a Wing Slat but moreover to conceive the most appropriate combination of the technologies for Wing Slat ice protection. These ‘Hybrid’ systems have been used successfully on horizontal stabilizers on smaller aircraft types, but further work is required in the application to larger platforms and wings.
In addition to the CfP scope, GKN would like to offer to integrate its own proven electro-thermal technology alongside the Associates’ electro-thermal and expulsive technologies to enhance the value of the integration activity and form a technology alliance to increase the probability of finding a successful solution.
In addition to functionality of the overall IPS the ‘actuation’ system aspects must be seamlessly integrated into the aircraft structure and electrical architecture. The current A320 slat is designed specifically to incorporate an engine bleed air IPS; therefore any change to this paradigm requires a carefully controlled design and integration approach and thorough understanding of wing performance requirements together with structural design ability in metallic and composite materials.
The final project deliverable is a modified A320 Wing Slat incorporating a Hybrid Electrical Ice Protection System.'