Modular Aircraft Fuselage Assembly for Removable Hydrogen Tanks

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Solution Overview

Problem

Existing aircraft designs with hinged doors for cryogenic hydrogen tanks are heavy and not designed for continuous load transfer, limiting their use in installing and removing major components like tanks, which increases weight and costs.

Innovation Solution

A fuselage structure with circumferential flanges and fastening means for a force-fit connection between fuselage sections, allowing easy assembly and disassembly of tanks, including hydrogen tanks, while ensuring continuous load transfer.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If hinged doors with latching mechanisms are used for loading and removal of tank components, then ease of operation is improved, but weight increases and device complexity increases

Engineering Contradiction:

Improveloading and removal of tank componentsVSAvoidweight of hinged door and latch mechanisms

Core Design Contradiction:

Ease of operationVSWeight of moving object

Solution Approach 1:

The fuselage is divided into modular sections that can be independently assembled and disassembled. The tank system is segmented into removable components that can be accessed through modular fuselage sections, eliminating the need for heavy continuous hinged doors while maintaining ease of component replacement.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The fuselage structure transitions from a static sealed design to a dynamic modular design where sections can be opened and closed. This allows the structure to adapt between operational integrity (sealed) and maintenance accessibility (open), reducing the need for heavy permanent door mechanisms.

Inventive Principle:

Principle #15Dynamics

2Ease of operation

If hinged doors are used for tank installation and removal, then ease of operation is improved, but device complexity increases due to continuous load transfer requirements

Engineering Contradiction:

Improveinstallation and removal of tanksVSAvoidcomplexity of load transfer mechanisms

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Inventive Principle:

Principle #15Dynamics

3Reliability

If heavy latching mechanisms are used for door closure, then reliability is improved, but weight increases

Engineering Contradiction:

Improvecontinuous load transferVSAvoidweight of latching mechanisms

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Inventive Principle:

Principle #15Dynamics

4Ease of manufacture

If modular fuselage sections with flanges are used for tank installation, then ease of manufacture is improved, but device complexity increases

Engineering Contradiction:

Improveassembly of fuselage sectionsVSAvoidcomplexity of flange and fastening means structure

Core Design Contradiction:

Ease of manufactureVSDevice complexity

Solution Approach 1:

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The modular fuselage sections with flanges serve multiple functions: structural integrity, ease of assembly, and access to tank components. This universal design approach consolidates what would otherwise require separate door mechanisms, latches, and structural elements into a unified system.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Data Source

PatentEP4699929A1Fuselage structure of an aircraft, method for assembling a fuselage structure and aircraft comprising a fuselage structure

Publication Date: 2026.02.25 AIRBUS OPERATIONS GMBH

Figure 1a~1b
Figure 2a~2b
Figure 3~4a

AI summary

The present invention provides a fuselage structure (100) of an aircraft, comprising: a first fuselage section (101) and a second fuselage section (102) connected to the first fuselage section (101), with the second fuselage section (102) comprising at least one first fuselage vessel (105a, b) extending the first fuselage section (101) in a longitudinal direction, with the first fuselage section (101) and the first fuselage vessels (105a) comprising circumferential flanges (111) arranged at longitudinal ends (120a, b) of the first fuselage section (101) and the first fuselage vessels (105a, b) extending radially in the first fuselage vessels (105a) and the first fuselage section (101) wherein a plurality of fastening means is provided extending through abutting flanges (111) of the first fuselage section (101) and the fuselage vessel (105a) to establish a force-fit connection between the first fuselage section (101) and the first fuselage vessels (105a), when assembled, and wherein the first fuselage vessel (105a) provides a storage space for at least one tank structure (107a, b), a method for assembling a fuselage structure (100) of an aircraft and an aircraft comprising such a fuselage structure (100).