DESIGN OF THE PARTITION
A lightweight composite sandwich partition was designed for the selected A320neo premium cabin configuration. The partition uses face sheets bonded to a honeycomb core, with the core trimmed to provide peripheral edge clearance and localized interface clearance around the mounting regions. The geometry follows the transverse curvature of the cabin sidewall while remaining clear of the central passenger circulation path. Seven mounting interfaces—three floor, two curved-side, one ceiling, and one auxiliary upper interface—were incorporated to provide distributed structural support and facilitate integration with the cabin environment.
PARTITION DIMENSIONS
The partition dimensions were derived from the reference A320/A320neo cabin cross-section and the selected premium seating arrangement. The overall profile was developed to conform to the available cabin envelope, with the curved side following the fuselage transverse curvature and the inner edge restricted to the seating zone without encroaching into the central passenger circulation path. The dimensional definition was established as a conceptual cabin-integration study using Airbus published reference geometry.
Reference: Airbus A320 Aircraft Characteristics — Aircraft Characteristics, Airport and Maintenance Planning
FACE SHEET DESIGN
The partition face sheet was designed as a thin composite skin forming the outer surfaces of the honeycomb sandwich panel. A 0.8 mm nominal thickness was selected for each face sheet, resulting in a 17.6 mm overall sandwich thickness with the 16 mm core. The face-sheet profile follows the selected cabin transverse curvature and incorporates the required edge and interface provisions. The two skins are intended to be bonded to the honeycomb core to provide a lightweight, stiff sandwich construction suitable for the conceptual aircraft interior application.
Design note: The 0.8 mm value is your conceptual design assumption, not an Airbus production specification. For an actual aircraft part, the laminate material, ply count/orientation, thickness, bonding system, and structural allowables would need to be established from the applicable approved material/process specifications and validated by analysis and testing.
INTERFACE LOCATIONS
Seven primary attachment interfaces were incorporated into the partition: three floor interfaces using conventional L-angle brackets, two curved-sidewall interfaces using curved brackets, and two upper interfaces using curved brackets—one connecting to the cabin ceiling and one providing auxiliary support near the stowage region. The curved brackets were developed to accommodate the local cabin curvature and maintain compatible mounting orientations. Local honeycomb clearance was provided around all bracket attachment regions to prevent interference with the sandwich core and facilitate mechanical attachment.
HONEYCOMB CORE DESIGN
A 16 mm thick hexagonal honeycomb core was designed between the two 0.8 mm face sheets, producing a nominal 17.6 mm sandwich-panel thickness. The core follows the partition's cabin-conforming profile and incorporates controlled perimeter edge clearance and localized clearance around the seven bracket interfaces. A simplified 60 mm cell size was used for CAD representation to manage computational complexity, while the final production core specification would be established through approved material data and structural validation.
Design Note: The 16 mm core thickness was selected as a conceptual design value to achieve the required sandwich-panel depth while maintaining a lightweight construction. The 60 mm honeycomb cell size was adopted solely to reduce CAD computational complexity during modeling and DMU integration. Final honeycomb material, density, cell size, core thickness, and mechanical properties would require selection from an approved aerospace material specification and validation through structural analysis and testing.
ASSEMBLY DETAILS
The partition was assembled as a lightweight three-layer sandwich structure consisting of two 0.8 mm face sheets bonded to a 16 mm honeycomb core, resulting in a nominal overall thickness of 17.6 mm. The honeycomb core is positioned between the skins using adhesive bonding to provide continuous load transfer and increased panel bending stiffness. Peripheral core clearance was incorporated for edge treatment, while localized core clearance was provided around the bracket interfaces to accommodate the mounting provisions. The resulting assembly combines a lightweight cellular core with thin structural skins to achieve an efficient strength-to-weight configuration.
Design Note: The assembly represents a conceptual aircraft-interior design for portfolio purposes. The adhesive system, surface preparation, bond-line thickness, edge-closeout method, local insert/reinforcement design, and manufacturing process would require definition from approved aerospace material/process specifications and subsequent structural and environmental qualification for an actual aircraft application.
NORMAL L-ANGLED BRACKET DESIGN
A conventional L-angle bracket was designed for the three floor interfaces of the partition. The perpendicular flanges provide a direct mechanical connection between the partition and cabin floor while providing lower positional restraint and load transfer. The simple bracket geometry facilitates fastening and installation while maintaining a compact interface with the sandwich panel.
CURVED BRACKET DESIGN
A geometry-conforming curved bracket was developed for the curved sidewall, ceiling, and stowage-region interfaces. The bracket profile follows the local cabin curvature while maintaining a suitable attachment orientation between the partition and surrounding cabin structure. Four curved brackets are incorporated to provide lateral and upper restraint and to distribute interface loads into the cabin structure.
NOTE:
For this portfolio demonstration, fastener holes and fastener hardware have intentionally not been modeled in the bracket and partition interfaces. The objective at this stage is to demonstrate the overall design methodology, interface definition, DMU integration, and installation-feasibility workflow rather than detailed fastener-level design. Therefore, the subsequent Interface Definition, DMU Integration, and Installation Feasibility stages will be evaluated using the defined bracket/interface locations without modeled holes or fasteners.