Rotorcraft Avionics Mounting Structure With Unitary Cabling
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Solution Overview
Problem
The existing methods for installing interface instruments and front avionics racks on a rotorcraft fuselage structure are time-consuming, complex, and difficult to standardize, especially in confined spaces, and do not easily allow for reorganization or weight reduction, while also complicating maintenance and increasing costs.
Innovation Solution
A mounting structure with a slotted body and unitary cabling assembly that simplifies the installation and communication of interface instruments and avionics racks, using segregated avionics connectors and a unitary cabling assembly that includes electrical and optical harnesses, allowing for easier assembly, reduced weight, and potential for upgrading, while avoiding overcomplication and simplifying the organization of the cockpit.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional separate mounting methods are used for interface instruments and avionics rack, then installation flexibility is maintained, but installation time increases and complexity increases
Solution Approach 1:
The patent combines the mounting of interface instruments and avionics rack into a single integrated mounting structure. The control panel and avionics rack are mounted together as one assembly, allowing both components to be installed simultaneously in a single operation, thereby reducing installation time and simplifying the mounting process while maintaining flexibility in component selection and configuration
2Weight of moving object
If traditional cabling methods are used, then connection flexibility is maintained, but weight increases and complexity increases
Solution Approach 1:
The patent integrates electrical and optical cabling into a single unified cabling assembly that is mounted together with the interface instruments and avionics rack. This consolidation reduces the total weight of cabling while simplifying the organization and routing of connections, as all cabling is managed through a single integrated structure rather than separate cable management systems
Solution Approach 2:
The integrated mounting structure serves multiple functions simultaneously: it provides mechanical support for both interface instruments and avionics rack, organizes and routes electrical cabling, and manages optical fiber connections. This multi-functional design eliminates the need for separate cabling management systems, reducing overall complexity and weight
3Adaptability or versatility
If detailed customization is applied to each mounting configuration, then adaptability is improved, but standardization decreases and costs increase
Solution Approach 1:
The patent divides the mounting structure into modular segments that can be independently configured. The interface instruments and avionics rack are mounted as separable components within the integrated structure, allowing customers to select and configure specific components based on their needs while using the same standardized mounting framework. This modular approach maintains adaptability without sacrificing standardization
Solution Approach 2:
The integrated mounting structure is designed as a universal platform that can accommodate various configurations of interface instruments and avionics rack. The standardized mounting interface and integrated cabling system can support different equipment combinations and configurations, allowing a single standardized design to serve multiple application requirements and reduce manufacturing costs through economies of scale
Data Source
AI summary
A rotorcraft fitted with means for mounting at least one front avionics rack (3, 3′) and man-machine interface instruments (2) on board a fuselage structure (4). A mounting structure (1) comprises a slotted body forming compartments for receiving interface instruments (2), the avionics rack (3, 3′), and a unitary cabling assembly (12) suitable for incorporating as a block with the mounting structure (1). The mounting structure (1) is installed as a block on the fuselage structure (4) after its functioning has been verified. The unitary cabling assembly (12) may also include separation connectors (14) segregating communications of the front avionics rack (3, 3′) respectively with remote computers (5) by means of a primary communications bus of the multiplexed, unidirectional, or bidirectional type, and with ancillary equipment (6) and/or with on-board instruments (7) by means of a secondary fieldbus.