Multi-spar Wing Port Box Joint Access Design
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Solution Overview
Problem
The use of access panels in aircraft with composite materials for accessing joints in multi-spar wing structures increases complexity and weight, counteracting the weight savings achieved by using composites, and complicates maintenance due to undesirable load distribution and limited access.
Innovation Solution
A multi-spar wing structure design where openings are alternated between two skin panels to provide access to all bays, improving load distribution and allowing for better airflow while maintaining structural integrity and facilitating maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If access panels are used to cover openings for accessing joints in multi-spar wing structures, then access to joints is provided, but the complexity of the horizontal stabilizer increases
Solution Approach 1:
The invention extracts the access function from separate access panels and integrates it directly into the skin panels by forming openings within the skin panel structure itself. This eliminates the need for additional access panels while maintaining access to joints, thereby reducing overall structural complexity.
Solution Approach 2:
The invention merges the access panel function with the skin panel structure by integrating openings directly into the skin panels. This combination eliminates separate access components and reduces the total number of parts in the horizontal stabilizer assembly.
2Strength
If access panels are designed to provide desired load bearing, then structural integrity is maintained, but the weight of the aircraft increases
Solution Approach 1:
The invention removes the need for heavy access panels by integrating access openings directly into the skin panels. This extraction of the access function eliminates redundant structural components and reduces overall aircraft weight while maintaining load bearing capability through the optimized skin panel design.
Solution Approach 2:
The invention changes the structural parameters of the skin panels by incorporating openings and associated reinforcement features directly into the skin panel design. This parameter change allows the skin panels to simultaneously provide access functionality and maintain load bearing capability without requiring additional heavy access panels.
3Ease of operation
If all openings are formed in one skin panel, then access to all bays is provided, but load distribution becomes unfavorable
Solution Approach 1:
The invention segments the access openings across multiple skin panels rather than concentrating all openings in a single skin panel. This segmentation distributes the structural impact across different panels, resulting in more favorable load distribution while still providing access to all bays through the distributed opening arrangement.
4Weight of moving object
If composite materials are used in horizontal stabilizers, then weight savings are achieved, but access to joints becomes more difficult
Solution Approach 1:
The invention incorporates access openings and associated features into the skin panel design during the preliminary manufacturing stage. This preliminary action ensures that access to joints is built into the composite structure from the beginning, maintaining ease of access while preserving the weight savings benefits of composite materials.
Solution Approach 2:
The invention extracts the access function from separate access panels and integrates it directly into the composite skin panels. This extraction eliminates the need for additional access components that would add weight, thereby maintaining the weight savings achieved through composite material usage while ensuring easy access to joints.
Data Source
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AI summary
A method for connecting a wing. A frame for a wing is positioned relative to a fuselage of an aircraft. The frame has bays and comprise a front spar, a rear spar, and a number of spars located between the front and rear spars. A first number of skin panels is on a first side of the frame, and a second number of skin panels may be on a second side of the frame. The first side is opposite to the second side. Openings are in the first and second numbers of skin panels. The openings are in locations such that each bay has an opening and such that the openings alternate between the first side and the second side between adjacent bays in the bays. The frame is attached to the fuselage using the openings to access an interior of the frame.