| 摘要 |
A device for protecting a computer of an aircraft turbine engine, the device comprising a box 34 containing the computer 30 and a cover 36 covering the box, the box being supported by tabs 38A-38D forming integral portions of the box and maintaining a flow of air between the bottom of the box and a portion of the casing 32 of the engine on which they are to come into secure contact via resilient studs 40A-40D, the box being made of a composite material. A plurality of connectors 42 may make external electrical connections through a wall of the box. The box may be covered by a layer of metal. The metal may be covered in intumescent paint. The computer may be a FADEC. |
