Aircraft Fuselage Space-Frame Venting for Hydrogen Leak Management
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Solution Overview
Problem
Existing hydrogen storage systems in aircraft face challenges in managing hydrogen tank failures, such as leaks or fires, which can lead to explosive gas mixtures and overpressure, while also requiring large amounts of inert gas for safety, increasing weight and reducing packaging efficiency.
Innovation Solution
A fuselage design with a non-load bearing outer skin and a space frame structure that includes openable skin areas, allowing controlled venting of compartments to prevent fluid accumulation and manage emergencies like hydrogen leaks or fires, maintaining aircraft maneuverability and aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If inert gas is stored in high amounts to prevent explosive gas mixtures, then safety is improved, but weight and packaging efficiency deteriorate
Solution Approach 1:
The invention extracts the harmful substance (hydrogen gas) from the fuselage interior by providing venting openings in the outer skin, allowing direct discharge to the external environment. This eliminates the need to store large amounts of inert gas for dilution purposes, thereby reducing weight while maintaining safety.
Solution Approach 2:
The invention converts the harmful accumulation of hydrogen gas into a beneficial venting mechanism. By designing the outer skin with openable areas that can be activated during emergencies, the system transforms potential danger into a controlled release mechanism, eliminating the need for inert gas storage.
2Reliability
If inert gas is used to flood tank regions to prevent explosive mixtures, then safety is improved, but the cryogenic liquid and gas remain trapped inside increasing weight
Solution Approach 1:
The invention provides venting openings in the outer skin that allow direct extraction and discharge of hydrogen gas and cryogenic fluids from the fuselage interior to the external environment. This eliminates the need to retain large quantities of fluid inside the fuselage, reducing weight while maintaining safety through controlled venting.
3Strength
If the outer skin is made load-bearing to maintain structural integrity, then strength is improved, but the ability to vent emergencies deteriorates
Solution Approach 1:
The invention segments the outer skin into multiple areas, with at least one area being configurable as openable for venting purposes. This segmentation allows the majority of the outer skin to maintain load-bearing structural integrity while specific segments can be opened to provide venting capability during emergencies.
Solution Approach 2:
The invention makes the outer skin dynamic by providing areas that can change from a closed state (maintaining structural integrity) to an open state (providing venting capability). The outer skin can be configured to be openable, allowing it to adapt between structural and venting functions as needed.
4Reliability
If skin areas are made openable for venting, then emergency handling is improved, but aircraft maneuverability may deteriorate
Solution Approach 1:
The invention segments the outer skin into multiple areas, with at least one area being configurable as openable for venting. This segmentation allows venting functionality to be provided without compromising the overall structural integrity and aerodynamic properties of the aircraft fuselage, thereby maintaining maneuverability.
Data Source
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AI summary
The present invention provides a fuselage (10) for an aircraft (1) or spacecraft, the fuselage (10) comprising: a first fuselage section (11) having a support structure with a load bearing outer skin (12); and a second fuselage section (13) having a non-load bearing outer skin (14) and a space frame structure (15) for supporting the non-load bearing outer skin (14), wherein the non-load bearing outer skin (14) comprises at least one skin area (16), which is configured to be openable for venting a compartment, which is at least sectionwise enclosed by the at least one skin area (16). Further the present invention provides an aircraft (1) or spacecraft comprising such a fuselage (10).