Rotatable Connection Arm for Tool-Free Aircraft Panel Reconfiguration
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Solution Overview
Problem
Existing aircraft interior paneling fastening systems require excessive cable length, leading to unwanted weight and inflexible configurations due to the need for manual disconnection and reconnection of electrical plug connections when reconfiguring cabin equipment, and they lack standardized interfaces for easy assembly and disassembly without tools.
Innovation Solution
A device featuring a rotatable connection arm that allows for the integration of an electrical contact device by adjusting its position by 180°, using a single or interchangeable connection pin to maintain a consistent interface, enabling flexible use with or without electrical contacts, and incorporating a damping element to prevent rattling noises.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If cables are extended to allow panel movement, then panel mobility is improved, but weight increases significantly
Solution Approach 1:
The patent extracts the electrical connection function from the mechanical fastening system by providing separate electrical plug connections that can be independently connected or disconnected. This allows the mechanical panel structure to be moved and reconfigured without being constrained by fixed cable routing, eliminating the need for excessive cable length while maintaining electrical connectivity when needed.
Solution Approach 2:
The patent segments the connection system into independent mechanical fastening components and electrical connection components. The mechanical fasteners (structure bracket, connection arm, spring clips) operate independently from the electrical plug connections, allowing the panel to be mechanically supported and positioned without requiring continuous cable routing, thus reducing overall system weight.
2Adaptability or versatility
If manual disconnection and reconnection of electrical plug connections is required, then reconfiguration flexibility is improved, but assembly time and complexity increase
Solution Approach 1:
The patent creates a universal interface system where the same structure bracket and connection arm mechanism serves both fastening functions and provides standardized mounting points for electrical connections. This standardized interface allows different panel configurations to use the same basic components, reducing assembly time through consistency while maintaining reconfiguration flexibility.
Solution Approach 2:
The electrical plug connections are designed to be pre-positioned and pre-connected to the panel structure during manufacturing. This preliminary action ensures that when the panel is installed, the electrical connections are already in place and functional, eliminating the need for time-consuming manual wiring during assembly or reconfiguration operations.
3Ease of manufacture
If standardized interfaces are implemented for all aircraft categories, then manufacturing efficiency is improved, but adaptability to different configurations decreases
Solution Approach 1:
The patent implements a dynamic connection system where the standardized structure bracket and connection arm assembly can be quickly reconfigured by changing the panel insert or electrical connection components. The standardized mechanical interface remains constant for manufacturing efficiency, while the interchangeable panel inserts and electrical plugs provide configuration adaptability for different aircraft categories and purposes.
Solution Approach 2:
The patent maintains standardized mechanical dimensions and interface geometries for the structure bracket and connection arm across all aircraft types, ensuring manufacturing efficiency. Meanwhile, configuration adaptability is achieved by changing electrical parameters (plug types, connection positions) and panel insert specifications, allowing the same basic structure to serve different flight categories without redesigning the core fastening mechanism.
4Ease of operation
If mechanical fastening systems are simplified for tool-free assembly, then ease of assembly is improved, but connection reliability may decrease
Solution Approach 1:
The patent incorporates a damping element in the form of a spring that is pre-installed in the connection arm. This spring provides beforehand cushioning by absorbing mechanical shocks and vibrations during operation, compensating for the simplified tool-free assembly design. The spring ensures reliable electrical contact maintenance and prevents rattling noises without requiring complex assembly procedures.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables simpler, more flexible reconfiguration of aircraft cabin equipment by reducing unnecessary cable length, minimizing weight, and ensuring reliable noise reduction through standardized interfaces that can be easily assembled and disassembled without tools, while accommodating electrical connections seamlessly.
Implementation Method 1
a spring clip (11) made from an elastic material and having a closed loop configuration with a clamping portion (111) and two opposing leg portions (112, 113)
Implementation Method 2
incorporating a damping element to prevent rattling noises
Data Source
AI summary
A connecting device (10) is provided for releasably connecting a fitting piece, such as an interior lining, to a supporting structure, such as a fuselage. The connecting device (10) includes a plug-in holding mechanism (50) including a bushing piece (52) and a connecting pin (75) that can be releasably locked therein. A bent connecting arm (60), to which the connecting pin is fastened, is releasably fastened to a structural holder (40) mounted on the supporting structure. In one position, the connecting arm (60) is plugged into the structural holder (40) and is releasably locked therein. In a second position (125), in which the connecting arm (60) is rotated 180° about the longitudinal axis thereof, an electrical contact device (90) is additionally inserted between the connecting arm (60) and the bushing piece (52). Hence, the same structural holder (40) and the same connecting arm (60) allow the fitting piece and the supporting structure to be connected to one another with or without connecting a contact device (90) therebetween.