Wing-Fuselage Truss Joint for Low-Bending Load Transfer
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Solution Overview
Problem
Current aircraft wing-fuselage joint connections face challenges with high manufacturing complexity, cost, and flexibility restrictions, requiring complex tooling and specialized analysis due to stress concentrations, while needing rapid assembly and disassembly for efficient wing removal.
Innovation Solution
A wing-fuselage truss joint assembly using multiple truss linkage elements in various orientations and planes to transfer shear forces in multiple directions, reducing bending moments and allowing rapid assembly/disassembly, incorporating pivotally connected truss members to manage aerodynamic, ground reaction, vibration, and thermal loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional pin joints are used to attach wing to fuselage, then structural strength is maintained, but manufacturing complexity and cost increase due to stress concentrations requiring complex tooling and specialized analysis
Solution Approach 1:
The wing-fuselage connection is segmented into multiple discrete truss members (upright members, diagonal members, lateral members) rather than using a single complex pin joint. Each truss member independently handles specific force components, dividing the complex connection problem into simpler, standardized components that reduce manufacturing complexity while maintaining structural strength.
Solution Approach 2:
The truss joint assembly acts as an intermediary structure between the wing and fuselage, introducing a framework of interconnected members that distribute and transfer loads. This intermediary truss structure eliminates the need for complex stress concentration management at a single pin joint interface, simplifying manufacturing while preserving load-bearing capacity.
2Stability of the object's composition
If traditional rigid connections are used, then structural stability is maintained, but assembly and disassembly time increases
Solution Approach 1:
The truss joint incorporates pivotable connections that allow dynamic adjustment and rapid assembly/disassembly. The upright members can pivot at the fuselage interface, and the entire truss assembly can be quickly installed or removed without permanent fastening, enabling rapid wing removal while maintaining structural stability during operation through the rigid geometry of the truss configuration.
3Manufacturing precision
If complex tooling is used for precise stress distribution, then manufacturing precision improves, but productivity decreases
Solution Approach 1:
The design transitions from managing stress concentrations through complex tooling to distributing loads through geometric configuration of multiple truss members. By changing the structural parameter from a single connection point to a distributed truss framework, the need for complex stress-distribution tooling is eliminated, improving productivity while maintaining precise load management through the inherent geometry of the truss members.
Data Source
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AI summary
A wing-fuselage truss joint assembly (100) for an aircraft includes joining members secured to the aircraft's wing and fuselage structures (104, 102). The joining members each include forward and aft wing joints (124, 136) and forward and aft fuselage joints (130, 140) connected by an upright member (110). The forward joining members are pivotally connected using interconnecting members (112) and the aft joining members are connected using aft truss members. The forward-right and aft-right joining members and the forward-left and aft-left joining members are connected by truss link members (120) and diagonal truss link members (114). The wing-fuselage truss joint assembly (100) is configured to reduce forces experienced by the wing from being transferred to the aircraft fuselage.