Composite Joint Transverse Flaps Load Continuity
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Solution Overview
Problem
In aircraft fuselage components with intersecting structural members, existing joint arrangements disrupt load continuity and require additional parts and complex assembly processes, leading to increased weight and manufacturing time.
Innovation Solution
A joint arrangement where transverse flaps from the laminations of one structural member are joined to the ends of intersecting segments of another, allowing load transmission without additional parts, facilitating a single-piece manufacturing process and weight optimization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If additional parts are used to join intersecting structural members, then load continuity is ensured, but device complexity and manufacturing time increase
Solution Approach 1:
The patent merges the joint function directly into the structural members themselves by creating transverse flaps from the laminations of the first member that join to the segments of the second member. This eliminates the need for separate additional joining parts while ensuring load continuity through the integrated flap structure.
Solution Approach 2:
The second structural member is segmented into two segments at the intersection zone, allowing each segment to be joined to the transverse flaps of the first member. This segmentation enables the joint arrangement to distribute loads effectively while maintaining continuity without requiring complex additional components.
2Reliability
If additional parts are used to join intersecting structural members, then load continuity is ensured, but weight increases
Solution Approach 1:
By merging the joining function into the structural members themselves through integrated transverse flaps, the patent eliminates the need for separate additional parts that would increase weight. The flaps are formed from the existing lamination material of the first member, optimizing weight while ensuring load continuity.
3Weight of stationary object
If complex tooling systems are used for single-piece manufacturing, then weight optimization is achieved, but manufacturing complexity increases
Solution Approach 1:
The transverse flaps are pre-formed as part of the lamination structure of the first structural member during its manufacturing process. This preliminary action allows the flaps to be ready for joining the segments of the second member without requiring complex additional tooling systems during final assembly, achieving weight optimization while controlling manufacturing complexity.
4Adaptability or versatility
If multiple parts are assembled, then design flexibility is maintained, but manufacturing time increases
Solution Approach 1:
The patent combines multiple structural members into a single integrated piece by forming transverse flaps that join the segments of the second member directly to the first member. This merging eliminates the need for separate assembly operations, reducing manufacturing time while maintaining the design flexibility of having intersecting structural members through the integrated flap configuration.
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 solution ensures continuous load transmission between intersecting structural members, reducing the number of parts and assembly operations, thereby minimizing weight and manufacturing time while enabling efficient production of optimized aircraft fuselage components.
Implementation Method 1
composite materials enable said combination to be achieved also by means of chemical bonding procedures
Data Source
AI summary
A joint arrangement for composite-material structural members in components including a skin and a plurality of structural members, applicable to pairs of first and second intersecting structural members, such as a beam and a frame in an aircraft fuselage, both members having a configuration which includes webs, inner flanges and outer flanges, in which, in the zone of intersection between said members, the laminations of one or both flanges of the first member include transverse flaps which are joined to one or both flanges of the ends of the segments of the second member which are separated at the intersection, acting as means for transmission of loads between them.