Aircraft Wing Stringer Weight Reduction via Machining
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Solution Overview
Problem
The existing methods for creating aircraft wing stringers, either through splicing or machining, face challenges of added weight and complexity due to the need for varying strength along the wing span, with limited modification possibilities in machining a single stringer.
Innovation Solution
A method involving a stringer blank with integral flanges, side panels, and a crown, where the lower surface of the flange is machined to modify the stringer's height along its length, and the crown's thickness is varied to optimize structural stability and reduce weight, using extrusion and machining to form a continuous stringer from metal or metal alloys.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If stringers are created by splicing or joining sections, then weight characteristics can be tailored to loading, but extra weight and complexity are added to the wing box
Solution Approach 1:
The stringer is divided into multiple extruded sections that can be joined together. Each section can have different cross-sectional characteristics tailored to the local loading conditions, while maintaining overall structural integrity through controlled joining processes
Solution Approach 2:
Different sections of the stringer have different cross-sectional properties (height, thickness, shape) optimized for the specific loading conditions at each location along the wing span. This allows weight reduction in low-load areas while maintaining strength where needed
2Weight of moving object
If a single stringer is machined to varying degree, then unnecessary weight is reduced, but the amount of modification is limited
Solution Approach 1:
The stringer is divided into multiple extruded sections that can be joined together. Each section can have different cross-sectional characteristics tailored to the local loading conditions, while maintaining overall structural integrity through controlled joining processes
Solution Approach 2:
The cross-sectional parameters of the stringer (height, thickness, shape) are varied along its length by using different extruded sections with optimized dimensions for each location, enabling significant weight reduction while maintaining structural requirements
3Strength
If stringer sections are spliced or joined, then weight characteristics are tailored, but extra weight is added to the wing box
Solution Approach 1:
The stringer is divided into multiple extruded sections that can be joined together. Each section can have different cross-sectional characteristics tailored to the local loading conditions, while maintaining overall structural integrity through controlled joining processes
Solution Approach 2:
Different sections of the stringer have different cross-sectional properties (height, thickness, shape) optimized for the specific loading conditions at each location along the wing span. This allows weight reduction in low-load areas while maintaining strength where needed
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 approach allows for optimized structural stability and reduced weight by tailoring the stringer's cross-section along its length, minimizing material usage and manufacturing complexity while maintaining necessary strength, thus improving efficiency and reducing overall weight.
Implementation Method 1
The stringer blank may be formed by extrusion
Data Source
AI summary
The present invention relates to a stringer for an aircraft wing and a method of forming such a stringer in which the stringer is formed from a single piece of material and then machined to optimise the dimensions and weight of the stringer.