Aircraft Fuselage Reinforcement Assembly for Large Panel Removal
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Solution Overview
Problem
The challenge of easily removing large removable panels from an aircraft fuselage while maintaining structural integrity and avoiding deformation, particularly for accessing and maintaining hydrogen tanks housed in the fuselage, is not adequately addressed by existing technologies.
Innovation Solution
A reinforcing assembly is used that includes a first support fixed to the exterior of the fuselage around an opening and a sub-assembly fixed to the removable panel, comprising upper and lower beams with crossmembers, and fixing elements to stabilize and reinforce both structures during panel removal.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a removable panel with area exceeding 20 m2 is removed from the fuselage to access hydrogen tanks, then maintenance accessibility is improved, but the fuselage structure is weakened and risk of deformation increases
Solution Approach 1:
The reinforcing assembly is installed on the fuselage before the removable panel is removed. The first support is fixed to the exterior face of the fuselage around the opening, and the sub-assembly with beams and crossmembers is fixed to the panel, preparing the structure in advance to withstand the stresses of panel removal and prevent deformation
Solution Approach 2:
The reinforcing assembly is divided into separate components: a first support fixed to the fuselage and a sub-assembly fixed to the panel. These segmented parts can be independently installed and removed, allowing the panel to be taken out for maintenance while the fuselage structure remains reinforced
2Strength
If reinforcing elements are permanently installed on the airframe to prevent deformation during panel removal, then structural integrity is improved, but the mass of the fuselage increases
Solution Approach 1:
The reinforcing assembly is designed to be temporarily installable and removable rather than permanently fixed. The first support can be fixed to the fuselage using fixing means such as brackets or dowel barrels, and the sub-assembly can be attached to the panel, allowing the reinforcement to be present only when needed for panel removal operations
Solution Approach 2:
The reinforcing assembly can be removed and reused after the panel removal operation is complete. The first support and sub-assembly are designed to be detachable, allowing the reinforcement elements to be recovered and stored for future use rather than remaining as permanent added mass on the fuselage
3Productivity
If the removable panel is designed to be easily removable for maintenance, then maintenance efficiency is improved, but the risk of fuselage or panel deformation during removal increases
Solution Approach 1:
The sub-assembly with second upper and lower beams is fixed to the removable panel before removal operations begin. This preliminary reinforcement ensures the panel can withstand the stresses of removal without deforming, while still allowing easy removal when needed
Solution Approach 2:
The reinforcing structure is segmented into a first support on the fuselage and a sub-assembly on the panel, connected through fixing elements. This segmentation allows independent reinforcement of each component, ensuring both the fuselage and panel maintain structural stability during the removal process
Data Source
AI summary
An assembly for reinforcing a fuselage of an aircraft, the aircraft including a fuselage including an opening and a removable panel received in the opening. The assembly including a first support fixed to an exterior face of the fuselage around and outside an opening in the fixed fuselage. A sub-assembly is to an exterior face of the removable panel and housed inside the first support. The first support is fixed to the fuselage. The sub-assembly is fixed to the removable panel.