Closed-Profile Aircraft Frame Shaping Skin
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Solution Overview
Problem
Current aircraft structure assembly methods require numerous connections and tools, leading to increased production time and cost due to geometric and dimensional constraints, and often necessitate the use of shims to compensate for angular defects, which complicates the assembly process.
Innovation Solution
The use of frames with a closed, hollow trapezoidal profile that can serve as a support for shaping the skin, eliminating the need for additional connecting elements and shims, as the frame's geometry allows it to be used as a tool for shaping the skin directly, reducing the number of assembly parts and constraints.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional open profile frames with clips and stabilizers are used, then structural connections are achieved, but the number of assembly elements and geometric constraints increases
Solution Approach 1:
The patent merges the functions of multiple separate components (frame, clip, stabilizer) into a single integrated closed-profile frame structure. The closed profile itself provides both the structural support and the shaping function, eliminating the need for separate clips and stabilizers, thus reducing assembly complexity while maintaining structural integrity.
Solution Approach 2:
The closed-profile frame serves multiple functions simultaneously: it provides structural support, acts as a shaping tool for the skin, and eliminates the need for separate connecting elements. This multi-functionality reduces the total number of components required in the assembly process.
2Manufacturing precision
If multiple connecting elements and shims are used, then assembly constraints are satisfied, but production time and cost increase
Solution Approach 1:
The patent extracts and eliminates unnecessary intermediate components (clips, stabilizers, shims) from the assembly process. By using the closed-profile frame directly as the shaping tool, it removes multiple assembly steps and the time-consuming installation of adjustment shims, thereby increasing productivity while maintaining precision.
Solution Approach 2:
The closed-profile frame is designed in advance with the exact geometry needed to serve as both the structural element and the shaping tool. This preliminary design integrates the shaping function into the frame itself, eliminating the need for subsequent adjustment operations and reducing production time.
3Ease of manufacture
If open profile frames with 90° sections are used, then manufacturing is simplified, but angular defects require shims for compensation
Solution Approach 1:
The patent transitions from symmetric 90° open profile sections to an asymmetric closed profile shape that is optimized for both manufacturing and function. The closed profile's continuous geometry eliminates the angular joints of open sections, preventing angular defects without requiring shims for compensation.
Solution Approach 2:
Instead of using open profiles that require closing with additional elements, the patent inverts the approach by using closed profiles as the primary structure. This inversion eliminates the inherent angular defects of open sections while maintaining ease of manufacture through the continuous, seamless geometry of the closed profile.
Data Source
Figure 1~4C
Figure 5~7B
Figure 8A~10
AI summary
The object of the invention is an aircraft structure comprising a skin (28) reinforced in two directions, by a first family of stiffeners called stringers (30) arranged along the longitudinal direction of the aircraft and by a second family of stiffeners called frames (32) arranged in planes perpendicular to the longitudinal direction and which ensure the transfer of orbital forces, characterized in that at least one frame (32) has a hollow section delimited by a closed profile, made for a given section in one piece, a portion of which is in contact with the skin.