Aircraft Fuselage Wedge Joint for Structural Continuity and Access
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Solution Overview
Problem
Existing orbital joints for aircraft fuselage sections are either complex and heavy, or not designed for easy maintenance access, posing challenges for accessing hydrogen tanks and other internal components.
Innovation Solution
A fitting structure comprising male and female wedge elements with a butt-strap, allowing easy attachment and separation of fuselage elements using self-aligning fasteners, ensuring structural continuity and facilitating access for maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional orbital joints with rivets are used to attach fuselage sections, then structural integrity and mechanical continuity are ensured, but the joint becomes complex and heavy, and difficult to disassemble for maintenance
Solution Approach 1:
The joint is segmented into discrete components: wedge elements (male and female), butt-strap, and fasteners. This allows the complex joint to be broken down into manageable parts that can be independently manufactured, assembled, and maintained, reducing overall system complexity while maintaining structural integrity
Solution Approach 2:
The wedge elements incorporate a tilted second portion that enables dynamic adjustment and guidance during assembly and disassembly. This dynamic feature allows the joint to be easily separated for maintenance while maintaining structural integrity during operation, resolving the contradiction between reliability and ease of maintenance
2Strength
If orbital joints are designed for strong mechanical continuity, then the elements must be in intimate contact with identical or perfectly complementary shapes, but this requires high manufacturing precision and increases complexity
Solution Approach 1:
The wedge elements are designed with self-aligning features where the tilted second portion automatically guides the male and female wedges into proper alignment during assembly. This self-aligning mechanism reduces the need for high manufacturing precision while ensuring strong mechanical continuity through the complementary wedge geometry
Solution Approach 2:
The wedge elements feature asymmetric geometry with a tilted second portion that creates a complementary fit between male and female elements. This asymmetric design provides guidance and alignment during assembly, reducing manufacturing precision requirements while maintaining strong mechanical continuity
3Strength
If heavy and complex mechanisms are used for orbital joints in cargo aircraft, then structural strength is ensured, but maintenance access to internal components becomes difficult
Solution Approach 1:
The joint system is segmented into removable wedge elements and a butt-strap that can be independently accessed and manipulated. This segmentation allows maintenance personnel to access internal components by removing specific joint elements without having to dismantle the entire structure, improving maintenance access while maintaining joint strength
Solution Approach 2:
The wedge elements incorporate a tilted second portion that enables easy insertion and removal through guided movement. This dynamic design allows rapid assembly and disassembly for maintenance purposes while the butt-strap provides continuous structural support, resolving the contradiction between joint strength and maintenance accessibility
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
Provides a robust and safe joint for aircraft fuselage elements that can be easily disassembled for maintenance, maintaining aerodynamic shape and ensuring structural integrity.
Implementation Method 1
each first wedge element comprising a first portion configured to be attached to an inner side of the first aircraft fuselage element and a second portion tilted with respect to the first portion
Data Source
Figure 1
Figure 2~3
Figure 4a~4b
AI summary
Fitting structure for aircraft fuselage configured to attach a first aircraft fuselage element (201) to a second aircraft fuselage element (202) along complementary section perimeters (100) of both aircraft fuselage elements (201, 202), wherein the fitting structure for aircraft fuselage comprises: a plurality of first wedge elements (101) distributed along a first section perimeter (100a) of the first aircraft fuselage element (201), and; a plurality of second wedge elements (102) distributed along a second section perimeter (100b) of the second aircraft fuselage element (202); and; at least one butt-strap (300) configured to cover an outer side of the first aircraft fuselage element (201) and an outer side of the second aircraft fuselage element (202) in correspondence with their complementary section perimeters (100).