Aircraft Fuel Tank with Vertical Spherical Caps for Crash Load Management
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Solution Overview
Problem
Existing aircraft fuel tanks lack optimal crashworthiness, particularly in vertical crash scenarios, and do not efficiently utilize fuselage volume.
Innovation Solution
The fuel tanks are arranged within the fuselage with a first cap portion facing the roof and a second cap portion facing the bottom, featuring a cylindrical or spherical shape, and are supported by support elements and cushion components to manage crash loads effectively.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional fuel tank arrangements are used in aircraft, then the fuselage volume can be filled, but the crashworthiness under vertical crash loads is insufficient
Solution Approach 1:
The fuel tank is designed with a spherical zone or cylindrical portion enclosed by cap portions, creating a rounded, curved geometry. This spherical/cylindrical shape inherently distributes vertical crash loads more effectively across the tank structure compared to conventional flat-bottomed tanks, improving crashworthiness while efficiently utilizing the available fuselage volume through its compact, space-efficient form.
Solution Approach 2:
The fuel tank employs an asymmetric orientation where the first cap portion faces the roof portion of the fuselage and the second cap portion faces the bottom portion, with the cylindrical portion positioned vertically. This asymmetric arrangement optimizes the tank's structural response to vertical crash loads by directing forces along its strongest axis, while simultaneously achieving efficient fuselage volume utilization through strategic positioning.
2Reliability
If the fuel tank is oriented with cap portions facing the roof and bottom of the fuselage, then vertical crash loads are better managed, but the installation complexity increases
Solution Approach 1:
The fuel tank is divided into distinct functional segments: a spherical zone or cylindrical portion for fuel storage, a first cap portion facing the fuselage roof, and a second cap portion facing the fuselage bottom. This segmentation allows each component to be optimized for its specific function while simplifying the overall installation process, as the modular design enables easier integration into the fuselage structure compared to a monolithic complex shape.
Solution Approach 2:
The fuel tank design integrates multiple functions into a single structure: the spherical zone or cylindrical portion provides fuel storage volume, the cap portions provide structural load-bearing surfaces for crash management, and the overall configuration enables efficient fuselage volume utilization. This multi-functionality reduces the need for additional separate components, thereby simplifying installation despite the optimized crash load management requirements.
Data Source
Figure 1~2b
Figure 2c~2d
Figure 3
AI summary
Disclosed is an aircraft 1 which comprises a fuselage 20 and, installed therein, at least one fuel tank 10. The fuel tank 10 has a tank wall comprising a spherical zone or a cylindrical portion 10c, and a first cap portion 10t and a second cap portion 10g enclosing the spherical zone or the cylindrical portion 10c, respectively. The first cap portion 10t of the at least one fuel tank 10 installed in the fuselage 20 faces a roof portion 20r of the fuselage, and its second cap portion 10g faces a bottom portion 20b of the fuselage. In particular, the aircraft 1 thus comprises an upright arrangement of the at least one fuel tank 10. Support elements 41, 42 may serve to support the at least one fuel tank 10 against a shell 22 and/or against at least one frame component 21, 21' of the fuselage 20.