Multi-lobe Cryogenic Tank with Internal Reinforcement Frame
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Solution Overview
Problem
Existing cryogenic tanks on aircraft are prone to rupture or dislodgment under inertia loads during flight operations, leading to potential leaks and damage, and are often too heavy or inefficient in volume usage.
Innovation Solution
A cryogenic tank design featuring a shell with intersecting partial cylinders and an internal reinforcement frame that distributes loads along multiple directions, providing structural robustness while maintaining lightweight and volume efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a cryogenic tank is made more structurally robust to withstand inertia loads, then reliability improves, but weight increases and volume efficiency decreases
Solution Approach 1:
The tank employs a multi-lobe shape formed by intersecting partial cylinders with domed ends, creating curved surfaces that naturally distribute stress during flight maneuvers. This geometric configuration provides structural robustness against inertia loads while maintaining a compact, space-efficient form factor suitable for aircraft integration
Solution Approach 2:
The tank utilizes composite material construction combining multiple materials with different properties to achieve high strength-to-weight ratio. This allows the tank to withstand extreme inertia loads during flight operations without the excessive weight that would result from using traditional monolithic metal constructions
2Reliability
If a cryogenic tank is made more structurally robust to withstand inertia loads, then reliability improves, but volume efficiency decreases
Solution Approach 1:
The multi-lobe configuration with intersecting cylindrical surfaces and domed ends creates a compact geometry that maximizes internal volume while maintaining external dimensions suitable for aircraft cargo spaces. The curved surfaces efficiently distribute stress, providing structural robustness without requiring excessive external volume
Solution Approach 2:
The tank is divided into multiple lobes formed by intersecting partial cylinders, with each lobe contributing to the overall structural integrity. This segmentation allows the tank to achieve high strength-to-volume ratio while efficiently utilizing the available space within the aircraft cargo hold
3Ease of manufacture
If traditional spherical or cylindrical tanks are used, then manufacturing is simpler, but volume efficiency is lower and more tanks are needed
Solution Approach 1:
While maintaining curved surfaces for structural efficiency, the multi-lobe configuration is achieved through intersecting partial cylinders that can be manufactured using standard fabrication techniques. The design balances manufacturing feasibility with optimized volume efficiency, allowing fewer tanks to be used compared to traditional spherical or cylindrical designs
Data Source
AI summary
A cryogenic tank includes a shell having an interior side, an exterior side, and an internal volume that is bounded by the interior side. The shell has a shape that includes at least two elongated lobes that are defined by partial cylinders that intersect each other. The partial cylinders extend lengths along central longitudinal axes that are offset from each other. The lobes include opposite domes that extend at opposite ends of the length of the corresponding partial cylinder. The cryogenic tank includes an internal reinforcement frame having a web of elongate frame members extending within the internal volume. The frame members extend along the interior side of the shell such that lengths of the frame members extend along paths that follow the profile of the interior side of the shell. The internal reinforcement frame is configured to distribute loads exerted on the shell along at least three different directions.