Composite Horizontal Airfoil Tip Fairing Weight Reduction
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Solution Overview
Problem
Traditional metal tip fairings for horizontal airfoils are heavy, complex to manufacture and maintain, and difficult to repair due to their multi-element structure, which complicates assembly and increases weight and drag.
Innovation Solution
A tip fairing made from a single composite material part with stiffening elements and a skin, manufactured using Resin Transfer Molding, featuring a C-channel design with all stiffening elements oriented in the same direction, reducing the need for soluble cores and allowing for lighter weight and simplified assembly, with integrated attachment spars and optional bronze mesh for lightning protection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional metal tip fairings are manufactured using multiple elements (skin, stringers, spars, rivets), then structural integrity and compatibility with the airfoil are achieved, but weight increases and manufacturing complexity increases
Solution Approach 1:
The patent combines multiple discrete metal elements (skin, stringers, spars, rivets) into a single integrated composite fairing structure. The composite material provides both structural integrity and weight reduction by eliminating the need for separate attachment elements while maintaining the necessary strength to withstand airfoil loads.
Solution Approach 2:
The patent employs composite materials (typically fiber-reinforced polymers) to manufacture the tip fairing, replacing traditional metal construction. Composite materials offer high strength-to-weight ratio, allowing the fairing to maintain structural integrity while significantly reducing weight compared to metal alternatives.
2Strength
If traditional metal tip fairings are manufactured using multiple elements, then structural integrity is achieved, but manufacturing and maintenance complexity increases
Solution Approach 1:
The patent integrates multiple functional elements into a single monolithic composite structure, eliminating the need for separate manufacturing and assembly processes for skin, stringers, spars, and rivets. This single-piece construction dramatically simplifies manufacturing while maintaining all necessary structural functions.
Solution Approach 2:
The composite fairing is manufactured as a single pre-assembled unit with all structural features built-in during the molding process. This preliminary integration of all elements into one component eliminates subsequent assembly steps and reduces manufacturing complexity.
3Strength
If traditional metal tip fairings are manufactured using multiple elements, then structural integrity is achieved, but repair difficulty increases
Solution Approach 1:
The integrated composite structure allows for simpler repair procedures compared to multi-element metal construction. Damage can be addressed by repairing or replacing the entire fairing as a single unit, avoiding the complexity of disassembling and reassembling multiple metal components with various tolerances and attachment requirements.
4Adaptability or versatility
If traditional metal tip fairings are used, then compatibility with the airfoil structure is achieved, but aerodynamic drag increases
Solution Approach 1:
Composite materials allow for greater design flexibility in creating smooth, continuous aerodynamic surfaces on the tip fairing. The material can be molded into optimized aerodynamic shapes that reduce drag while maintaining compatibility with the underlying airfoil structure, unlike rigid metal construction which requires additional fairing elements to achieve smooth surfaces.
Data Source
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AI summary
The present invention relates to a tip fairing (200) of a horizontal airfoil of an aircraft, comprising stiffening elements (202) and a skin (203) covering the stiffening elements (202), the stiffening elements (202) comprising a central web and two flanges located at the tips of the web, contact between the skin (203) and the stiffening elements (202) being made through the flanges of the stiffening elements (202), characterized in that it is manufactured from a composite material, it is manufactured from a single part, and the planes defining the webs of any pair of stiffening elements (202) taken in twos form an angle less than 30°.