Divided Internal Frames for Aircraft Repair Without Internal Access
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Solution Overview
Problem
Conventional aircraft repair methods introduce aerodynamic penalties that compromise efficiency and regulatory compliance due to external patches, especially in structures without internal access.
Innovation Solution
A system comprising a divided frame with U-shaped portions and straps, secured with blind fasteners, is installed internally to repair aircraft structures without disrupting airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If external patches are applied to repair damaged sections, then structural integrity is restored, but aerodynamic efficiency deteriorates due to increased drag and altered airflow
Solution Approach 1:
The frame is divided into two separate portions that can be independently positioned and attached to the internal structure. This segmentation allows the repair components to be installed from the interior without requiring external access, thereby maintaining the external aerodynamic surface while restoring structural integrity through internal reinforcement.
Solution Approach 2:
The repair solution transitions from an external two-dimensional patch application to an internal three-dimensional frame structure. By moving the repair mechanism into the internal volume of the aircraft structure, the solution eliminates external aerodynamic interference while providing robust structural support through the spatial configuration of the divided frame portions and connecting straps.
2Ease of repair
If conventional repair methods are used on structures without internal access, then structural damage can be addressed, but aerodynamic performance is significantly compromised
Solution Approach 1:
Instead of applying repairs from the external surface inward, this invention inverts the repair approach by installing the frame structure from the internal side outward. The divided frame portions are positioned internally and connected through straps, allowing complete repair functionality to be achieved without any external access or external visible components, thereby preserving aerodynamic efficiency.
3Strength
If a complete frame is installed internally, then structural reinforcement is achieved, but installation becomes impossible without internal access
Solution Approach 1:
The frame is divided into two portions that can be separately introduced through existing access points and then assembled internally using connecting straps. This segmentation enables installation in structures without internal access, as the components can be fed through external openings and connected from the interior, achieving full structural reinforcement without requiring internal workspace.
Solution Approach 2:
The divided frame portions and connecting straps are designed to be assembled in a nested sequence within the constrained internal space. The straps connect the two frame portions after they are positioned, allowing the complete reinforced structure to be constructed within the existing aircraft structure's internal volume, maximizing space utilization and eliminating the need for internal access.
Data Source
Figure 1
Figure 2~3
AI summary
The system for repairing aircraft structures comprises a frame (2) that is divided into two portions, and in that the system also comprises one or more straps (3) that attach both portions of the frame (2) to each other. The method comprises the steps of making a cutout in the skin (1) of the structure to be repaired; dividing the frame (2) into two portions; placing the two portions of the frame (2) on the internal side of the skin (1) through said cutout; and attaching the two portions of the frame (2) to each other by one or more straps (3). They permit the installation of an internal frame in a structure of an aircraft without internal access.