INTERFACE DEFINITION
Seven mechanical interface locations were defined between the partition and the surrounding cabin structure. Three L-angle brackets provide floor attachment, while two curved brackets interface with the cabin sidewall. A further curved bracket provides the ceiling attachment, and an additional curved bracket near the stowage region provides supplementary upper support. The interface locations were positioned according to the local cabin geometry and integrated with the honeycomb core clearance regions to provide a practical load-transfer and mounting arrangement.
Design Note: The interface definition represents the conceptual mechanical architecture of the partition. Fastener holes, fastener hardware, and detailed joint sizing were intentionally omitted from this portfolio study. The defined interfaces are therefore used for subsequent DMU integration and installation-feasibility assessment at the component/interface level. Detailed fastener design, local reinforcement, joint loads, and structural sizing would be addressed during the detailed-design stage.
CONCEPTUAL CABIN INTERIOR DESIGN
A conceptual aircraft cabin interior was developed to provide the surrounding environment required for the DMU (Digital Mock-Up) integration and installation-feasibility study of the designed partition. The cabin model was created using publicly available aircraft reference data, with the geometry simplified to represent the major spatial and interface elements relevant to the study.
The conceptual cabin includes the cabin floor, curved fuselage/sidewall, cabin ceiling, overhead stowage, passenger seating, and surrounding cabin structures. These elements establish the primary spatial boundaries against which the partition position, clearances, and interface locations can be evaluated.
Design note: The cabin interior shown is a conceptual representation developed specifically for portfolio-level DMU integration. It is derived from publicly available aircraft data and is not intended to reproduce the OEM production cabin configuration or detailed aircraft structure. Therefore, the results demonstrate the CAD/DMU integration methodology and design approach, rather than certification-level aircraft installation.
DMU INTEGRATION
The designed partition was integrated into the conceptual aircraft cabin DMU to evaluate its spatial compatibility with the surrounding cabin environment. The partition was positioned between the cabin zones and checked against the cabin floor, curved sidewall, ceiling, overhead stowage, passenger seating, and nearby cabin structures.
Design Note: This DMU is a conceptual integration model developed using publicly available aircraft reference data. Detailed production-level fasteners, attachment holes, internal aircraft structure, and certification-specific installation details are intentionally excluded from this demonstration.
DMU Integration – Verification Checks
01. Clash Detection
The integrated partition was checked against the surrounding cabin components to identify potential geometric clashes or interferences. Particular attention was given to the cabin sidewall, floor, ceiling, overhead stowage, and passenger seating envelope.
02. Clearance Verification
Available clearance around the partition was visually evaluated to ensure that the structure remains within the intended cabin envelope. The checks focused on maintaining separation from seats, stowage, ceiling, sidewall, and adjacent cabin structures.
03. Accessibility & Movement
The partition location was reviewed for installation and maintenance accessibility, considering access to the defined interface locations. The surrounding passenger area and conceptual cabin arrangement were also checked to ensure that the partition does not introduce obvious restrictions to passenger movement or access through the cabin.
DMU Result:
The conceptual integration provides a preliminary verification of clash-free positioning, adequate clearance, interface accessibility, and movement compatibility. These checks are intended for portfolio-level design demonstration and would require detailed aircraft data and installation constraints for production-level validation. The validated configuration was then taken forward for installation-feasibility assessment.
INSTALLATION FEASIBILITY
The installation feasibility of the partition was evaluated using the integrated conceptual cabin DMU. The assessment focuses on whether the partition can be practically positioned and installed within the available cabin space while maintaining its defined interfaces and surrounding clearances.
01. Installation Access
The accessibility of the floor, sidewall, ceiling, and stowage interface locations was reviewed to ensure that the partition can be positioned and attached without obvious obstruction from adjacent cabin components.
02. Installation Path & Movement
The partition was evaluated for a feasible installation approach and movement path within the cabin. The surrounding seats, sidewall, ceiling, stowage, and other cabin elements were considered to ensure that the partition can be brought into its intended position without significant geometric interference.
03. Interface & Clearance Verification
The final installed position was checked to confirm that the partition maintains the required interface alignment and surrounding clearances. The assessment also considered potential interference with passenger seating and cabin circulation.
04. Feasibility Outcome
Based on the conceptual DMU assessment, the partition demonstrates a feasible installation configuration within the defined cabin environment, with accessible interface locations and no obvious geometric obstruction along the conceptual installation path.
Design Note: This is a conceptual installation-feasibility assessment based on the simplified DMU. Detailed fasteners, installation tooling, aircraft primary structure, tolerance stack-up, and certification-specific installation requirements are outside the scope of this demonstration.
