ASSEMBLY OF A FIXED INTERNAL STRUCTURE OF A TURBOJET ENGINE NACELLE AND THERMAL PROTECTION PANELS

摘要

The invention relates to an assembly of a fixed internal structure (54) of a turbojet engine nacelle (2) and thermal protection panels (640, 642), said fixed internal structure (54) comprising an inner face (540), on which the thermal protection panels (640, 642) are mounted, and an outer face (542) constituting a portion of the inner surface of a cold stream flow path (52), the assembly being characterised in that it comprises at least one attachment element (68) of a first panel (640) and of an adjacent second panel (642), the attachment element (68) making it possible to secure the first and second panels (640, 642) to each other in a junction area, the attachment element (68) not being rigidly attached to the internal fixed structure (54).