Composite Cargo Door Panel Assembly for Aircraft Conversion
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Solution Overview
Problem
Existing methods for converting passenger aircraft into freighter aircraft are inefficient and economically unfeasible for composite fuselages, as they require cutting and replacing large sections of the fuselage, leading to waste and high costs.
Innovation Solution
A panel assembly made from composite materials, including a cargo opening and reinforced frames, is fabricated to replace the removed section, using splices to secure it to the existing fuselage, reducing waste and fabrication costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a traditional method is used to create a large opening with reinforced thicker skin for a metallic aircraft P2F conversion process, then the conversion can be achieved, but this method is not applicable for composite aircraft and requires cutting and replacing large sections of the fuselage leading to waste and high costs
Solution Approach 1:
The fuselage is divided into modular sections with standardized joining seams that allow for precise panel removal and replacement. This segmentation enables targeted conversion of specific sections without requiring removal of entire fuselage sections, thereby reducing material waste while maintaining manufacturing feasibility for composite aircraft.
Solution Approach 2:
The invention utilizes composite materials with integrated joining seams that are specifically designed for P2F conversion. These composite panels incorporate pre-formed joining seams that align with existing fuselage structure, enabling efficient replacement without the need for extensive cutting and welding, thus reducing both waste and manufacturing complexity.
2Productivity
If an entire fuselage barrel is fabricated from composite material with a large opening for cargo door, then the conversion can be achieved, but the remaining portion of the newly fabricated barrel must be scrapped which is not economically feasible
Solution Approach 1:
Instead of fabricating an entire fuselage barrel, the invention employs pre-fabricated composite panels with integrated cargo door openings that are inserted into existing fuselage sections. This segmentation approach allows only the necessary panels to be replaced while retaining the majority of the original fuselage structure, eliminating the need to scrap large portions of newly fabricated material.
Solution Approach 2:
The composite panels with cargo door openings are pre-fabricated with joining seams that are pre-aligned to match existing fuselage structure. This preliminary preparation of discrete panels rather than entire fuselage sections enables efficient conversion by replacing only the necessary portions, thereby maintaining productivity while minimizing material loss.
3Ease of manufacture
If composite fuselage barrel has an integral one-piece skin panel wound by a composite tape winding machine, then the fuselage can be manufactured, but there are no existing seams for use in selecting a panel for removal which requires cutting in an appropriate location
Solution Approach 1:
The integral one-piece skin panel is divided into multiple sections with pre-formed joining seams during the composite tape winding process. These joining seams are strategically positioned to align with existing fuselage structure, enabling easy panel removal and replacement without requiring complex cutting operations, thus simplifying the conversion process while maintaining manufacturing efficiency.
Solution Approach 2:
The composite fuselage structure incorporates localized joining seams at specific positions along the skin panel that are optimized for panel removal. These local quality features are integrated during the winding process to create predetermined separation lines that facilitate clean panel separation, reducing the complexity of cutting operations while maintaining the overall structural integrity of the fuselage.
Data Source
AI summary
A panel assembly for an aircraft can include a composite material skin with a cargo opening sized to receive cargo into the fuselage of the aircraft and to remove the cargo from the fuselage of the aircraft. The panel assembly can include curved panel edge frames coupled with the outer skin and disposed on opposite lateral sides of the cargo opening in the outer skin. Upper and lower sill beams can be disposed on opposite upper and lower sides of the cargo opening in the outer skin. The upper and lower sill beams each can be coupled with the panel edge frames. The upper and lower sill beams can be coupled with curved aircraft frames that are disposed inside the fuselage of the aircraft to secure the outer skin to the aircraft at a panel opening in the fuselage of the aircraft.