Stiffened Fuselage Component with Irregular Node Angles
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Solution Overview
Problem
Aircraft fuselage components made from fiber reinforced composite materials face challenges in achieving optimal weight and load-bearing capacity, as existing designs often require rigid intersections between ribs and stringers, leading to inefficiencies in weight distribution and manufacturing complexity.
Innovation Solution
A stiffened fuselage component featuring a skin element with elongated stiffening elements forming an irregular pattern with node points at acute or obtuse angles, allowing for adaptive weight and load-bearing capacity optimization, and incorporating omega-shaped stiffeners with internal cavities for reduced weight and integrated functional elements like electric or fluid lines, manufactured using a method that co-cures the skin and stiffening elements with a thermoset plastic material.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If rigid intersections between ribs and stringers are used, then structural stability is improved, but weight increases and manufacturing complexity increases
Solution Approach 1:
The patent applies asymmetry by using acute or obtuse angled intersections between stiffening elements instead of traditional rigid right-angled intersections. This asymmetric configuration allows the structure to achieve structural stability through geometric distribution of loads rather than rigid mechanical connections, thereby reducing weight while maintaining stability.
Solution Approach 2:
The patent implements local quality by creating an irregular pattern of stiffening elements where each node point has unique angular characteristics tailored to local load requirements. This allows optimization of structural stability at specific locations without requiring rigid intersections throughout the entire structure, reducing overall weight.
2Stability of the object's composition
If rigid intersections between ribs and stringers are used, then structural stability is improved, but device complexity increases
Solution Approach 1:
The asymmetric angular intersections simplify manufacturing by eliminating the need for precise right-angled alignment and complex joining fixtures. The acute and obtuse angles can be more easily formed and assembled, reducing device complexity while maintaining structural stability.
3Ease of manufacture
If regular grid pattern of stiffening elements is used, then manufacturing simplicity is improved, but adaptability decreases
Solution Approach 1:
The patent uses local quality by implementing an irregular pattern where each node point has specific acute or obtuse angles tailored to local structural requirements. This allows the structure to adapt weight and load-bearing capacity to specific functional needs while remaining manufacturable through standardized curing processes.
Solution Approach 2:
The patent applies parameter changes by varying the angular parameters (acute and obtuse angles) and spatial distribution of stiffening elements to optimize weight and load-bearing capacity for different application requirements, while the overall irregular pattern approach maintains manufacturing simplicity through co-curing.
4Strength
If solid stiffening elements are used, then strength is improved, but weight increases
Solution Approach 1:
The patent applies porous materials by incorporating hollow internal cavities within the stiffening elements. These cavities reduce the weight of the stiffening elements while maintaining their load-bearing capacity through optimized wall thickness and geometric configuration, achieving strength-to-weight optimization.
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
The solution enables a weight-optimized fuselage component with enhanced load-bearing capabilities and simplified manufacturing, allowing for tailored structural reinforcement and efficient integration of functional elements, while reducing tooling costs and design complexity.
Implementation Method 1
a curable material may be injected into the laminate construction. Finally, the injected curable material and/or the curable material applied onto the surfaces of the fibers may be cured under pressure and/or raised temperature
Implementation Method 2
producing a composite material having a matrix of a cured synthetic material and reinforcing fibers embedded in the matrix
Data Source
Figure 1
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AI summary
A stiffened fuselage component (10) made of a fiber reinforced composite material, in particular for use in an aircraft, comprises a skin element (12) and a plurality of elongated stiffening elements (18) forming a stiffening element pattern comprising a plurality of node points (20) and being attached to an inner surface (16) of the skin element (12), wherein at least some of the node points (20) are defined by an intersection of at least two stiffening elements (18) at an acute angle or an obtuse angle, and wherein at least some of the elongated stiffening elements (18) are shaped so as to define an internal cavity (22) delimited by an inner surface (24) of the stiffening elements (18) and covered by the skin element (12).