Aircraft Fuselage Panel Welding Flexibility
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The existing welding techniques for assembling aircraft fuselage panels result in a loss of flexibility, as longitudinal welding between panels deprives the fuselage of necessary adjustability during assembly.
Innovation Solution
An assembly process where the longitudinal ends of welded edges are not linked, and longitudinal virolas are fixed to partially cover the concave surface of the panels, allowing for flexibility and adjustability during assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If longitudinal welding is performed between panels along the entire joining line, then structural strength and continuity are improved, but flexibility and adjustability during assembly are lost
Solution Approach 1:
The welded joint is segmented into two distinct zones: a first zone with full longitudinal welding for structural strength, and a second zone at the longitudinal end with no welding to preserve flexibility. This segmentation allows the fuselage to have both strong connected sections and flexible adjustment zones during assembly.
Solution Approach 2:
Different welding qualities are applied at different locations along the panel joint. The first longitudinal zone receives complete welding for maximum strength, while the second longitudinal zone at the panel end remains unwelded to maintain flexibility. This local differentiation resolves the contradiction between overall strength and end flexibility.
2Manufacturing precision
If complete longitudinal welding is performed between panels, then manufacturing precision and alignment are improved, but ease of operation during assembly deteriorates
Solution Approach 1:
The assembly process is segmented into phases: first, panels are aligned with welding in the first longitudinal zone to ensure precision; second, the unwelded second zone at the panel end allows manual adjustment and repositioning. This segmentation enables both precise alignment where needed and operational flexibility where adjustment is required.
Solution Approach 2:
The joint transitions from a static fully-welded state to a dynamic partially-welded state, where the unwelded end zone allows panels to be moved and adjusted during assembly operations, improving ease of operation while maintaining alignment precision in the welded zone.
3Stability of the object's composition
If longitudinal ends of welded edges are connected, then structural integrity is improved, but flexibility of the fuselage is reduced
Solution Approach 1:
The longitudinal edge connection is segmented into a first zone with welding for structural integrity and a second zone at the panel end without welding for flexibility. This segmentation maintains overall structural integrity while preserving necessary flexibility at the panel ends during assembly.
Solution Approach 2:
Different connection qualities are applied locally: the first longitudinal zone has welded connections for structural integrity, while the second longitudinal zone at the panel end has no welding to maintain flexibility. This local quality differentiation resolves the contradiction between overall integrity and end flexibility.
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
The proposed assembly process enhances the flexibility of the fuselage, enabling better adjustment and alignment of fuselage sections during assembly, while maintaining structural integrity.
Implementation Method 1
at least two panels (10, 12) are positioned contiguously and assembled by edge-to-edge welding along a joining line (17A) of the panels (10, 12)
Data Source
Figure 1~2
Figure 3
Figure 4
AI summary
The present invention aims to provide a method for assembling aircraft panels by welding that improves their flexibility. Panels (26, 28) are butted together along longitudinal seams and joined to each other by their longitudinal edges (30, 32) by welding, without the longitudinal ends (30A, 30B, 32A, 32B) of their welded edges (30, 32) being joined together. Longitudinal ferrules (38, 40) are attached so as to partially cover the concave surface of the panels (26, 28), at least partially at said ends (30A, 30B, 32A, 32B). The absence of welding at the ends provides the desired flexibility. The present invention also covers fuselage sections formed by assembling panels according to this method, as well as the aircraft comprising such sections.