Aircraft Frame Component Integrally Produced Metal Sheet
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Solution Overview
Problem
Current frame components for aircraft fuselage structures are complex to produce and mount efficiently, lacking in mechanical rigidity, and require multiple components and assembly steps.
Innovation Solution
A frame component with a C-shaped cross-section produced integrally from a metal sheet, featuring a central web, inner web, and outer web, with reinforcing formations at stringer recesses to enhance flexural rigidity, allowing for simple and efficient production and assembly into a closed frame structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional frame components are produced using multiple separate parts and assembly steps, then structural flexibility is improved, but manufacturing complexity and production time increase
Solution Approach 1:
The patent merges the central web, inner web, and outer web into a single integrated frame component produced from one metal sheet. This consolidation eliminates the need for multiple separate parts and assembly steps, directly reducing manufacturing complexity while maintaining the structural flexibility needed for aircraft fuselage applications
2Ease of repair
If traditional frame components are produced using multiple separate parts, then ease of repair is improved, but productivity and assembly efficiency decrease
Solution Approach 1:
The integrated design combines multiple web elements into a single produced component, enabling rapid production of high-piece numbers through streamlined manufacturing processes. The single-metal-sheet construction eliminates assembly steps while maintaining repairability through the component's overall design
3Ease of operation
If stringer recesses are formed in the outer web, then ease of operation is improved, but mechanical rigidity decreases
Solution Approach 1:
The patent applies local reinforcement at the stringer recess locations by forming reinforcing formations (such as beads or raised structures) on the central web at these critical positions. This localized strengthening maintains the overall mechanical rigidity and flexural strength of the frame component while preserving the stringer recesses for easy stringer installation and alignment
Data Source
AI summary
A frame component for a frame of a fuselage structure of an aircraft includes a central web extending along a longitudinal direction and having an inner edge region with respect to a radial direction running transversely with respect to the longitudinal direction and an outer edge region with respect to the radial direction. An inner web is bent from the inner edge region of the central web towards a first side. An outer web is bent from the outer edge region of the central web towards the first side. The central web, the outer web and the inner web are produced integrally from a metal sheet and together define a C-shaped cross section of the frame component. At least one stringer recess is formed in the outer web and in the outer edge region of the central web. The central web has, in the region of the stringer recess, a first reinforcing formation which forms a protrusion on the first side of the central web.