Composite Preform Assembly via Synchronous Layup and Compaction
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Solution Overview
Problem
Current methods for fabricating aircraft airframe components are labor-intensive and inefficient, often relying on hand-layup processes or single-head Automated Fiber Placement machines, which limit productivity and quality in producing composite parts with complex geometries.
Innovation Solution
A method and system for assembly line fabrication of airframe components using fiber-reinforced broad goods, where sheets are trimmed, rotated, and delivered synchronously to multiple stations to form layup patterns corresponding to aircraft contours, which are then placed and compacted onto a mandrel to create preforms, allowing for rapid and precise construction of composite parts.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If hand-layup processes are used, then flexibility and adaptability are maintained, but labor intensity increases and productivity decreases
Solution Approach 1:
The airframe component is divided into multiple discrete components (stringers, spars, skins, frames) that can be fabricated separately and then assembled. This segmentation enables parallel fabrication processes, significantly increasing overall productivity while maintaining design flexibility through modular assembly.
Solution Approach 2:
A stationary cell system serves as an intermediary platform that integrates multiple fabrication operations. The cell contains positioning mechanisms, tooling, and equipment that enable automated or semi-automated fabrication processes while maintaining the flexibility of hand-layup methods, thus bridging the gap between manual and fully automated approaches.
2Productivity
If single-head AFP machines are used, then equipment complexity is reduced, but fabrication time increases and productivity decreases
Solution Approach 1:
The airframe structure is segmented into discrete components that can be fabricated simultaneously in parallel using multiple AFP heads or different fabrication methods. This segmentation allows the system to manage complexity by breaking down the overall fabrication task into manageable sub-tasks that can be executed concurrently.
Solution Approach 2:
The system transitions from sequential single-head fabrication to parallel multi-component fabrication by adding spatial dimensionality. Multiple components are fabricated simultaneously in different locations within the stationary cell, effectively multiplying productivity without proportionally increasing system complexity.
3Manufacturing precision
If discrete components are assembled manually, then adaptability to design changes is maintained, but labor intensity increases and quality consistency decreases
Solution Approach 1:
The discrete components are designed with self-aligning features and standardized interfaces that enable precise assembly through the assembly process itself. The components 'self-correct' positioning errors and automatically achieve proper alignment, reducing the need for highly skilled manual intervention while maintaining quality consistency.
Solution Approach 2:
Manual measurement and alignment processes are replaced with automated positioning systems, computer-controlled assembly jigs, and digital tracking. This substitution of mechanical manual operations with automated systems ensures consistent quality while maintaining the ability to adapt to design changes through software control.
Data Source
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AI summary
A method for fabricating a preform (194) for a portion of an aircraft (1902) includes acquiring a sheet (118) of broad good fiber reinforced material, trimming the sheet to form layup pieces (116) having boundaries (119), placing the boundaries (119) into alignment, arranging the layup pieces (116) in a layup pattern (174) to form a ply (175), performing a placement operation that transports the layup pattern (174) onto a layup tool (190), and shaping the layup pattern (174) into conformance with a contour of the layup tool (190).