Aircraft Fuselage Frame Mounting With Snap-In Modular Carriers
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Solution Overview
Problem
The installation of equipment components in the interior of an aircraft, particularly in cramped underfloor regions like the triangle region, is cumbersome and time-consuming due to the need for multiple holders and tools, and manufacturing-induced dimensional deviations complicate the process.
Innovation Solution
A modular structural system comprising carrier elements, elongate frame elements, and coupling devices that allow for a snap connection, enabling pre-assembly outside the aircraft and efficient attachment to the fuselage structure, with adjustable coupling devices to compensate for dimensional deviations and simplify the installation process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple dedicated holders and brackets are provided for integrating system components into structural elements, then the components can be securely mounted, but the installation becomes cumbersome and time-consuming
Solution Approach 1:
The patent applies universality by designing a standardized carrier element with a universal coupling interface that can accommodate multiple different system components (ducts, pipes, electrical lines) through a single standardized mounting mechanism. This eliminates the need for multiple dedicated holders and brackets, allowing secure mounting of various components while significantly reducing installation time and complexity
Solution Approach 2:
The patent applies segmentation by dividing the mounting system into modular components: standardized carrier elements attached to structural elements, and interchangeable coupling devices that attach to system components. This modular segmentation allows for efficient pre-assembly and streamlined installation while maintaining secure mounting through standardized interfaces
2Ease of manufacture
If components are installed one after another inside the fuselage in cramped space, then installation can be performed, but the process becomes cumbersome and time-consuming
Solution Approach 1:
The patent applies preliminary action by enabling system components to be pre-assembled with their carrier elements and coupling devices outside the aircraft fuselage. This pre-assembly can be performed in a workshop environment with better accessibility, and then the pre-assembled units are installed as complete modules inside the fuselage, dramatically improving installation efficiency while maintaining feasibility in cramped spaces
Solution Approach 2:
The patent applies merging by combining multiple installation steps into a single operation. The carrier element, coupling device, and system component are integrated into a unified pre-assembled module that is installed as one unit, eliminating the need for sequential installation of individual components and thereby improving productivity
3Ease of operation
If a plurality of different brackets and tools are provided for efficient installation, then installation can be performed, but the complexity and time requirement increase
Solution Approach 1:
The patent applies universality by designing a standardized carrier element with a universal coupling interface that can accommodate multiple different system components (ducts, pipes, electrical lines) through a single standardized mounting mechanism. This eliminates the need for multiple dedicated holders and brackets, allowing secure mounting of various components while significantly reducing installation time and complexity
Solution Approach 2:
The patent applies self-service through the snap-in coupling mechanism that enables self-aligning and self-locking of components to the carrier elements. The coupling devices are designed to automatically position and secure themselves without requiring complex alignment procedures or specialized tools, thereby simplifying the installation process while maintaining ease of operation
Data Source
AI summary
A structure system for installation into a fuselage structure in an interior of an aircraft. The system has a first carrier element, a second carrier element, an elongate frame element having a first end and a second end, a first attachment device for attaching the first carrier element to the fuselage structure or to an element coupled with the fuselage structure, a first coupling device mounted to the first end for coupling the first carrier element to the frame element, and a second coupling device mounted to the second end for coupling the second carrier element to the frame element. The frame element holds a component to be installed in the interior. The first carrier element couples with the first coupling device, the second carrier element couples with the second coupling device, and one of the coupling devices snaps into the respective carrier element.