Abstract: A method for splicing honeycomb core together to form a core structure, such as an acoustic panel for an aircraft. The core structure may comprise a first honeycomb core, a second honeycomb core, and an intermediate bonding part disposed between the first and second honeycomb cores. The intermediate bonding part may comprise a syntactic core wrapped with or sandwiched between a non-foaming film adhesive. The syntactic core sandwiched between a first and second layer of film adhesive and a first and second honeycomb core is then compressed by vacuum and cured to bond the honeycomb cores together, forming the core structure.

Abstract: A method for splicing honeycomb core together to form a core structure, such as an acoustic panel for an aircraft. The core structure may comprise a first honeycomb core, a second honeycomb core, and an intermediate bonding part disposed between the first and second honeycomb cores. The intermediate bonding part may comprise a syntactic core wrapped with or sandwiched between a non-foaming film adhesive. The syntactic core sandwiched between a first and second layer of film adhesive and a first and second honeycomb core is then compressed by vacuum and cured to bond the honeycomb cores together, forming the core structure.

Abstract: Aircraft systems including thrust reversers with monolithic components are described herein. An aircraft system in accordance with one embodiment includes a thrust reverser having a fan duct inner wall section, a fan duct outer wall section radially outward of the fan duct inner wall section, and a connecting wall section extending between the fan duct inner wall section and the fan duct outer wall section. The fan duct inner wall section, the fan duct outer wall section, and the connecting wall section form a monolithic member.

Abstract: A computer-implemented method for providing on-line ultrasonically scanned images of composite parts for immediate feedback in a manufacturing environment is discussed. The scanned images are edited to indicate each deficiency that has been repaired on a previously assembled composite part. Quality assurance personnel enter data associated with each composite part and verify the data content. Repair personnel enter data associated with correcting an identified deficiency of the composite part. Historical data suitable for developing statistics and trends are stored for each type of composite part. When queries are launched, the statistical and trend data is filtered to produce reports that are displayed. That is, reports are generated that identify particular statistics and trends. The scan image and data associated with a composite part are linked together for cross-referencing and stored in a database that is accessible by client and server computers on a network.

Abstract: An acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a honeycomb-core material (74) sandwiched therebetween. The acoustic panel (26) includes an integral forward ring (36) and integral wedge fairings (44).

Abstract: An improved acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a new reinforcement structure, or pre-cured doubler (62) therein. The pre-cured doubler (62) is arranged to receive a load applied to the acoustic panel (26), and includes a face sheet (64) connected to a structural attachment area (52) of the perforated composite inner sheet (54). A structurally-reinforced core (63) is connected the face sheet (64). Preferably, the width of the face sheet (64) in an air flow direction of the acoustic panel (26) is substantially equal to the width of the structurally reinforced core (63) in the air flow direction. The pre-cured doubler (62) provides increase acoustic area in parts of the acoustic panel adjacent to attachment fittings (46). Expanded epoxy (87a) is also used to reinforce side edges and selected areas of the acoustic core (60) for the acoustic panel (26).