ASSEMBLY OF INTERNAL FIXED STRUCTURE OF TURBOJET 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) having an internal face ( 540), on which are reported the thermal protection panels (640, 642), and an outer face (542) constituting a portion of the inner surface of a cold flow vein (52), the assembly being characterized in that it comprises at least one fastening element (68) of a first panel (640) and a second panel (642) adjacent, the fastening element (68) for securing the first and second panels (640). , 642) to one another at a junction zone, the fastening element (68) not being integral with the internal fixed structure (54).