Honeycomb noise attenuation structure

Claim 1

An acoustical honeycomb sandwich panel for use as supporting structure within an aircraft jet engine inlet and nacelle structures wherein said acoustical honeycomb sandwich panel is exposed to the sound of jet engines and other noise producing mechanisms comprising: a honeycomb core having a multiplicity of open cells with walls of thin sheet material disposed transversely to the panel; a perforated facing of thin sheet material having one surface thereof bonded to one core face; an imperforate facing of thin sheet material bonded to the other core face; and a thin sheet of porous fibrous material bonded to the other surface of said perforated facing sheet with a bonding medium selected from a class of electrically insulating adhesive systems whose melt viscosity, during the curing process, is sufficiently high so that the adhesive will not flow into the pores of the porous sheet by capillary attraction whereby to maintain the full porosity of the porous fibrous material over the holes in said perforate facing sheet and insulating said thin sheet of porous fibrous material from said peforated facing sheet, the pores of said porous material providing communication between the core cells and the atmosphere through the perforations of said perforated sheet.