Adjustable Fuselage Brace for Repair Load and Deflection Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional devices for bracing aircraft fuselages during repairs are large, inflexible, and limited to specific station locations, requiring extensive bracing and often interfering with aircraft systems, making them cumbersome and inefficient.
Innovation Solution
A brace system with adjustable legs, pivot points, and actuator-controlled attachment assemblies that can be installed at various locations along the fuselage, allowing for precise load and deflection control using sensors and actuators, and can be easily transported and installed without interfering with internal systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional large static cradles are used for bracing, then structural support is provided, but the device complexity and difficulty of installation increase
Solution Approach 1:
The brace is divided into multiple independent legs (first leg, second leg, third leg) that can be separately positioned and adjusted. Each leg can be independently coupled to the fuselage at different locations, allowing the system to provide comprehensive structural support while maintaining modularity and reducing overall device complexity.
Solution Approach 2:
The brace incorporates actuators that enable dynamic adjustment of leg positions and orientations. This dynamic capability allows the brace to adapt to different fuselage configurations and damage locations, providing flexible structural support without requiring a complex fixed structure.
2Strength
If conventional cradles are used, then bracing is provided, but adaptability to different locations is limited
Solution Approach 1:
The brace is designed as a universal support system that can be installed at various locations along the fuselage. The multiple legs with adjustable positioning mechanisms and various coupling options enable the same brace structure to adapt to different damage scenarios and locations, providing versatile bracing capability.
Solution Approach 2:
The dynamic adjustment capabilities through actuators allow the brace to be reconfigured for different installation locations and fuselage geometries, enhancing adaptability while maintaining effective bracing.
3Strength
If extensive bracing is used to compensate for bulkhead damage, then structural integrity is maintained, but interference with aircraft systems occurs
Solution Approach 1:
The brace applies support forces at specific localized points along the fuselage rather than requiring extensive widespread bracing. The multiple legs can be positioned to target specific structural areas needing support, maintaining structural integrity while minimizing the physical footprint and reducing interference with aircraft systems.
Solution Approach 2:
The adjustable and reconfigurable nature of the brace allows it to be precisely positioned to provide structural support without interfering with sensitive aircraft systems. The dynamic positioning capabilities enable avoidance of windows, sensors, and other critical components.
4Strength
If large cradles and beams are built each time for new repairs, then adequate support is provided, but loss of time increases
Solution Approach 1:
The modular leg structure can be quickly assembled and configured for different repair scenarios without requiring custom-built large cradles each time. The standardized components reduce preparation time while maintaining adequate support.
Solution Approach 2:
The actuator-controlled dynamic adjustment capabilities allow rapid reconfiguration of the brace for different repair situations, eliminating the time-consuming process of building custom static cradles for each new repair.
Data Source
AI summary
The present disclosure provides a brace having a first leg and a second leg offset from the first leg. The brace also has a pivot assembly having a bar pivotably coupled with the first leg to define a first pivot point and pivotably coupled with the second leg to define a second pivot point. The brace further includes first and second attachment assemblies coupled with the first leg and the second leg, respectively, and each arranged to couple to a portion of a structure. In addition, the brace includes an actuator assembly coupling the first leg with the second leg and having an actuator arranged to pivot, or maintain a position of, the first leg relative to the first pivot point and to pivot, or maintain the position of, the second leg relative to the second pivot point so as to control a load on, and deflection of, the structure.