Composite Aircraft Panel Repair via Segmentation
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Solution Overview
Problem
The repair of large area damage on one-piece composite aircraft components is challenging due to the high cost and time required for replacing entire barrel sections, making existing methods impractical for quick return to service.
Innovation Solution
A method for repairing damaged composite aircraft components involves designing and fabricating customized composite replacement panels that include integrated replacement skin and stiffening substructure, using a custom layup mandrel tool for layup and curing, and mechanically fastening the replacement panel to the existing structure, allowing for efficient repair of large damaged areas without replacing entire sections.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If entire barrel section is removed and replaced, then structural integrity is restored, but repair time and cost increase significantly
Solution Approach 1:
The repair process segments the damaged component into three parts: the remaining intact barrel section, the removed damaged panel assembly, and the newly fabricated replacement panel. This allows only the damaged portion to be replaced rather than the entire barrel section, significantly reducing repair time while maintaining structural integrity through proper joining of the segmented components.
Solution Approach 2:
The damaged panel assembly is extracted (removed) from the barrel section, allowing the damaged area to be replaced without removing the entire barrel section. This extraction principle enables selective replacement of only the necessary components, reducing repair time and resource consumption while restoring structural integrity.
2Reliability
If entire barrel section is removed and replaced, then structural integrity is restored, but manufacturing cost increases significantly
Solution Approach 1:
The repair approach segments the replacement work into fabricating only the damaged panel assembly rather than an entire barrel section. This segmentation of the manufacturing scope reduces material consumption, fabrication time, and associated costs while still restoring the structural integrity of the aircraft component.
Solution Approach 2:
By extracting and replacing only the damaged panel assembly rather than the entire barrel section, the manufacturing cost is reduced proportionally to the reduced volume of materials and labor required, while the structural integrity of the critical load-bearing barrel section is preserved and restored.
3Reliability
If production schedule is disrupted for barrel section replacement, then damage is properly repaired, but productivity decreases
Solution Approach 1:
Segmenting the repair to affect only the damaged panel assembly minimizes production schedule disruption compared to replacing an entire barrel section. This localized repair approach maintains aircraft productivity and availability by reducing the downtime associated with fabrication and installation operations.
Solution Approach 2:
The replacement panel assembly can be fabricated in advance while the aircraft is in service or during scheduled maintenance windows, allowing the actual replacement operation to be performed quickly with minimal disruption to production schedules, thereby maintaining high aircraft availability and productivity.
Data Source
Figure 1
Figure 2A~2B
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AI summary
A randomly damaged area of a one-piece composite component of an aircraft is repaired according to a method herein. The damaged area covers skin and underlying stiffening substructure of the component. The method includes generating a design of a customized composite replacement panel for replacing the damaged area. The design includes replacement skin and underlying co-cured replacement stiffening substructure. The method further includes fabricating the composite replacement panel according to the design.