Low-Profile Aircraft Door Articulated Hinge for Fuselage Space
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Solution Overview
Problem
Conventional hinge assemblies for translating-motion-type aircraft doors are bulky and occupy significant space within the fuselage, limiting its availability for other purposes due to the mechanical linkage extending into the interior.
Innovation Solution
An articulated hinge assembly with a low-profile design that includes a hinge arm and linkage assembly to control the door's movement along a programmed path, incorporating an emergency power assist mechanism to ensure smooth operation and emergency opening.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a conventional mechanical linkage is used to control door rotation, then the door can be controlled to move along a programmed path, but the linkage occupies significant space within the fuselage interior
Solution Approach 1:
The patent removes the bulky mechanical linkage from the fuselage interior by integrating the door control function directly into the hinge assembly. The hinge members are configured with specific geometric relationships and pivot points that inherently guide the door along the desired programmed path without requiring separate control linkages extending into the cabin space.
Solution Approach 2:
The control function previously performed by separate mechanical linkages is merged into the hinge assembly itself. The hinge members incorporate the motion control geometry directly into their structure, combining the support function and the path control function into a single integrated mechanism that eliminates the need for additional space-consuming components.
2Ease of operation
If a bulky mechanical linkage is used to extend into the fuselage interior, then the door movement can be controlled, but the space available for other purposes such as stowage and seating is reduced
Solution Approach 1:
The patent extracts the door control function from the fuselage interior space by incorporating it into the hinge assembly located at the door edge. The hinge members are designed with built-in geometric constraints that provide programmed path control without requiring any components to extend into the passenger cabin volume.
Solution Approach 2:
The patent relocates the control mechanism from the interior volume of the fuselage to the exterior hinge assembly at the door edge. By moving the control geometry to a different spatial location (from interior to exterior), the design preserves all fuselage interior space while maintaining full door control capability.
3Volume of moving object
If a low profile hinge assembly is used, then space utilization within the fuselage is optimized, but the complexity of controlling door movement along a programmed path increases
Solution Approach 1:
The patent achieves programmed path control through carefully selected geometric parameters of the hinge members, such as pivot point locations, member lengths, and angular relationships. By optimizing these dimensional parameters, the design provides precise door movement control without requiring complex mechanical linkages, achieving both low profile and controlled motion.
Solution Approach 2:
The hinge members are designed with asymmetric geometric configurations where the pivot points and member dimensions are specifically tailored to guide the door along the desired programmed path. This asymmetric design allows the low-profile hinge assembly to inherently control door movement through its geometry rather than requiring additional symmetric control mechanisms.
Data Source
AI summary
An articulated hinge assembly for connecting a door to a fuselage of an aircraft includes an articulated hinge arm having a first hinge member pivotably coupled to a second hinge member at an elbow. The first hinge member includes a fuselage fitting pivotably coupled to a fuselage bracket. The second hinge member includes a door fitting pivotably coupled to a door bracket of the door. The articulated hinge assembly includes a linkage assembly coupled to the articulated hinge arm, the fuselage fitting and the door fitting. The linkage assembly includes a hinge linkage assembly coupled to the articulated hinge arm and the fuselage fitting and controlling movement of the hinge members relative to each other and relative to the fuselage fitting. The linkage assembly includes a door linkage assembly coupled to the articulated hinge arm and the door to control positioning of the door between open and closed positions.