Acoustic panel type noise insulating structure for use in inner wall of nacelle of turboshaft engine of aircraft, has notch formed on part of circumference of insert, and damping interface provided between body and insert

摘要

The structure (301) has a body (211) comprising a honeycomb structure (208) filled with filler resin (209). The body extends around a metal insert (207). The insert comprises an opening (201) that is utilized for receiving a fastening screw (202), and a notch (210) is formed on part of circumference of the insert. A damping interface (302) is provided between the body and the insert, where the damping interface extends over entire circumference of the insert.