Aircraft Fuselage Removable Structural Panel for Load-Transfer Access
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Solution Overview
Problem
Existing aircraft designs with hinged doors and latching mechanisms for large cryogenic tanks are heavy and not designed for continuous load transfer, limiting their use for frequent installation and removal of major components like hydrogen tanks.
Innovation Solution
A fuselage design with a removable structural panel and a locking structure that ensures continuous load transfer by using symmetrical lock fittings and lock parts with tapered profiles for alignment and positive-locking connections, allowing efficient insertion and removal of tanks without damaging the primary structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If hinged doors with latching mechanisms are used for tank access, then ease of operation is improved, but weight increases and continuous load transfer capability deteriorates
Solution Approach 1:
The fuselage access system is segmented into a removable structural panel that can be separated from the main fuselage structure. This panel includes lock fittings and lock parts that enable independent removal and installation, dividing the access function from the primary load-bearing structure while maintaining operational ease.
Solution Approach 2:
The structural panel is extracted as a separate, removable component from the fuselage primary structure. This extraction allows the panel to be removed completely for tank access while the remaining fuselage structure maintains its integrity and load transfer capability, eliminating the need for heavy hinged doors.
2Ease of operation
If hinged doors with latching mechanisms are used for tank access, then ease of operation is improved, but structural integrity deteriorates
Solution Approach 1:
The access system is segmented into a removable panel that separates the access function from the primary structure. The panel includes integrated lock fittings and lock parts that provide secure attachment during installation while allowing complete removal when needed, preserving fuselage structural integrity.
Solution Approach 2:
The structural panel is extracted as a discrete component that can be completely removed from the fuselage. This extraction ensures that the primary fuselage structure remains intact and maintains its load transfer capability, unlike hinged doors that require permanent attachment points.
3Strength
If structural panel with locking structure is used, then load transfer capability is improved, but device complexity increases
Solution Approach 1:
The locking structure is segmented into discrete lock fittings attached to the fuselage and corresponding lock parts on the panel. This segmentation allows for straightforward assembly and disassembly while maintaining load transfer capability through the distributed locking points.
Solution Approach 2:
The lock fittings and lock parts feature asymmetric tapered profiles that guide proper alignment during installation. The tapered geometry provides self-aligning characteristics that simplify the assembly process while ensuring correct positioning for load transfer.
4Adaptability or versatility
If removable structural panel is used for tank installation, then adaptability is improved, but manufacturing precision requirements increase
Solution Approach 1:
The lock fittings and lock parts incorporate asymmetric tapered profiles that provide self-aligning characteristics during assembly. The tapered geometry guides the panel into correct positioning, compensating for minor manufacturing variations and reducing precision requirements.
Solution Approach 2:
The lock fittings are pre-attached to the fuselage structure at predetermined locations before panel installation. This preliminary positioning establishes reference points that guide the panel alignment and reduce the precision required for final panel fabrication.
Data Source
Figure 1~2b
Figure 2c~3
Figure 4a~5
AI summary
The present invention provides a fuselage (101) of an aircraft (100), comprising a front portion (102) and a rear portion (103), with at least one opening (106) provided in the rear portion (103), with the opening (106) being closeable by a structural panel (107) fully removeable from the opening (106), wherein a locking structure (109) for the structural panel (107) is provided in the opening (106) and configured to transfer loads between a primary structure (108) of the fuselage (101) and the structural panel (107), a for closing an opening (106) of a fuselage (101)and an aircraft (100) having such a fuselage (101)..