Continuous Wing Stringer Structure for Swept Wing Assembly
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Solution Overview
Problem
Aircraft wing assemblies with traditional swept wing configurations are heavy due to the use of expensive and labor-intensive titanium materials in side of body joints, which increases weight and reduces fuel efficiency.
Innovation Solution
The implementation of a continuous wing structure with a progressively sweeping planform, featuring stringers with curved portions made from composite materials, which are formed using a ply layup device and stringer forming tools to reduce weight and complexity, allowing for a lighter and more efficient wing design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional titanium side of body joints with multiple fasteners are used, then structural integrity is ensured, but weight increases and fuel efficiency decreases
Solution Approach 1:
The patent replaces traditional titanium side of body joints with composite material joints that maintain structural integrity while significantly reducing weight. The composite joints use fiber-reinforced materials configured to withstand flight loads, achieving the same reliability function with reduced mass.
Solution Approach 2:
The patent integrates multiple separate fastening components into a single monolithic joint structure. Instead of using multiple fasteners distributed across upper and lower panel joints, the composite joint consolidates these functions into one piece, reducing overall weight and complexity.
2Strength
If traditional titanium side of body joints with many fasteners are used, then robust attachment is achieved, but manufacturing complexity and cost increase
Solution Approach 1:
The patent combines multiple separate fastening components into a single monolithic joint structure. Instead of using multiple fasteners distributed across upper and lower panel joints, the composite joint consolidates these functions into one piece, reducing overall weight and complexity.
Solution Approach 2:
The patent extracts and eliminates the need for multiple individual fasteners from the traditional joint design. By using composite material bonding and integration techniques, the fastening function is achieved without the complex assembly of numerous separate metal fasteners.
3Ease of manufacture
If traditional swept wing configuration with sharp angle is used, then simple manufacturing is achieved, but aerodynamic inefficiency increases
Solution Approach 1:
The patent implements a progressively sweeping planform where the sweep angle varies continuously along the span rather than being a fixed sharp angle. This dynamic geometric variation optimizes aerodynamic performance at different span locations while remaining manufacturable using composite molding techniques.
Solution Approach 2:
The patent replaces the traditional sharp angled sweep with a curved, progressive sweep pattern. The wing planform features smooth curvature transitions instead of abrupt angle changes, improving aerodynamic flow characteristics while maintaining manufacturing feasibility through composite tooling.
Data Source
AI summary
A wing structure for use with an aircraft is provided. The wing structure includes at least one wing section including an inboard portion, an outboard portion angled rearward from said inboard portion, and at least one stringer including a curved portion that extends across an interface defined between the inboard portion and the outboard portion. The curved portion has a radial curvature such that the at least one stringer extends continuously along the inboard portion and the outboard portion.