Continuous Hydrogen Tank in Aircraft Wing Spars
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Solution Overview
Problem
Conventional aircraft wing designs for hydrogen storage face challenges in achieving high gravimetric efficiency due to the weight of individual tanks and hydrogen leakage through connections, which compromises the overall storage efficiency and introduces fatigue in tank connections.
Innovation Solution
The aircraft wing incorporates a continuous storage tank with a serial array of hollow elongate tank portions and connecting portions, where each tank passes through apertures in internal spars, minimizing the need for discrete tanks and reducing weight and hydrogen leakage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If multiple individual tanks are used in the wing, then structural support is provided, but hydrogen leakage occurs through connections and gravimetric efficiency is compromised
Solution Approach 1:
The patent merges multiple individual tanks into a single continuous storage tank that extends through the wing structure. This eliminates the connections between multiple tanks, thereby preventing hydrogen leakage through threads and welds while maintaining structural support through the integrated design.
Solution Approach 2:
The continuous storage tank serves multiple functions simultaneously: it provides structural support for the wing, stores gaseous hydrogen, and eliminates leakage paths. The tank wall itself acts as both a structural element and a containment barrier, achieving multi-functionality that resolves the contradiction between structural support and hydrogen leakage prevention.
2Strength
If multiple individual tanks are used in the wing, then structural support is provided, but gravimetric efficiency is compromised
Solution Approach 1:
By combining multiple separate tanks into one continuous tank, the patent eliminates the weight of additional connection structures, supports, and sealing mechanisms required for multiple discrete tanks. The single continuous tank provides the same structural support with reduced total weight, improving gravimetric efficiency.
3Quantity of substance
If tanks are connected in a linear array, then storage capacity is increased, but high bending moments cause fatigue in connections
Solution Approach 1:
The patent merges multiple tank sections into a single continuous tank wall, eliminating the connections between discrete tanks. This removes the source of fatigue in connections while maintaining the storage capacity through the extended continuous structure that spans multiple spar locations.
4Stress or pressure
If hemispherical or domed ends are used in storage tanks, then stress distribution is improved, but total weight increases
Solution Approach 1:
The patent segments the storage tank into multiple elongate portions of constant cross-section separated by connecting portions. This segmentation allows the tank to achieve adequate stress distribution through the connecting portions while avoiding the weight penalty of hemispherical ends, as the constant cross-section portions provide sufficient structural integrity.
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
This design enhances gravimetric efficiency by reducing tank weight and minimizing hydrogen leakage, while also improving resilience to wing flexing without causing damage or leakage to the tanks.
Implementation Method 1
The tank wall is elastically deformed to absorb the energy of impact
Implementation Method 2
The tank wall is elastically deformed to absorb the energy of impact
Data Source
AI summary
A storage tank for gaseous hydrogen includes a continuous tank wall defining a serial array of hollow elongate tank portions of substantially constant cross-section and hollow connecting portions defining an internal storage volume, wherein adjacent ends of any pair of adjacent hollow elongate tank portions are connected by a hollow connecting portion having a cross-sectional dimension smaller than those of the adjacent hollow elongate tanks portions. The tank may be included in an aircraft wing such that it extends spanwise through one or more internal spars of the wing, thus providing a continuous gas storage volume at a given chordwise position notwithstanding the spars, and providing for storage of gaseous hydrogen at higher gravimetric efficiency than is achievable by a plurality of coupled discrete tanks disposed between the spars.