Stitched Carbon Fiber Aircraft Skin for Lightweight Frame Integration
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Solution Overview
Problem
Aircraft skins made of aluminum or aluminum alloys are heavy, reducing fuel efficiency and cannot be stitched to a structural frame.
Innovation Solution
A composite assembly for a blended wing body aircraft using carbon fiber materials stitched together with a resin matrix, forming an outer skin that is attached to a skeletal frame.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If aluminum or aluminum alloy is used for aircraft skin, then structural strength is maintained, but weight increases reducing fuel efficiency
Solution Approach 1:
The patent applies composite materials by combining carbon fiber reinforcement with resin matrix to create an aircraft skin that is both lightweight and structurally strong. This composite structure replaces traditional aluminum alloys, achieving weight reduction while maintaining or enhancing mechanical properties suitable for aircraft applications.
2Ease of manufacture
If aluminum or aluminum alloy is used for aircraft skin, then ease of manufacture is maintained, but ability to stitch to structural frame is lost
Solution Approach 1:
The patent changes the material parameters by selecting resin-based composite materials with specific properties that enable stitching. The resin matrix provides adhesiveness and bonding capability that allows the composite skin to be stitched to the structural frame, a capability that aluminum alloys lack due to their metallic bonding characteristics.
Data Source
AI summary
A composite assembly for an aircraft, the composite assembly including a first carbon fiber material structured for a portion of an outer skin surface of an aircraft, a second carbon fiber material stitched to the first carbon fiber material, wherein the second carbon fiber material is structured for a structural component of the aircraft, and wherein the stitching is configured to bind the first carbon fiber material and the second carbon fiber material, and wherein the aircraft further includes a single deck, wherein a cargo compartment and a passenger compartment are located on or above the single deck.