Wing Attachment Layout Using Lateral Rods for Narrower Mast Structures
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Solution Overview
Problem
Existing aircraft wing attachment systems face challenges in managing forces and torques, particularly along the longitudinal direction, which can lead to increased width and reduced aerodynamic performance when attempting to distribute these forces evenly.
Innovation Solution
Incorporation of a lateral connecting rod in the wing attachment system that extends between the primary structure and the wing, providing an additional path for force transfer and reducing stress on the primary structure while maintaining aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the wing attachment system uses multiple connecting elements distributed along the mast to manage forces and torques, then the force distribution improves, but the width of the primary structure increases
Solution Approach 1:
The patent introduces a lateral connecting rod that extends in the lateral direction (Y-axis) between the primary structure and the wing, creating a new spatial dimension for force transfer. This lateral arrangement allows forces to be distributed through a different geometric configuration, reducing the need to increase the longitudinal width of the primary structure while maintaining effective force management.
Solution Approach 2:
The wing attachment system is divided into multiple independent connecting elements: forward wing attachments, intermediate wing attachment, rear wing attachment, and lateral connecting rods. Each element handles specific force components, allowing the system to distribute loads efficiently without requiring a uniformly wide primary structure. The segmentation enables localized force management at different positions along the mast.
2Object-generated harmful factors
If the primary structure width is reduced to improve aerodynamic performance, then aerodynamic efficiency improves, but the ability to distribute forces and torques deteriorates
Solution Approach 1:
By introducing lateral connecting rods that extend perpendicular to the main longitudinal axis, the system creates additional force transfer pathways in the lateral dimension. This allows the primary structure to maintain a narrow width for aerodynamic efficiency while the lateral rods provide the necessary structural leverage for force distribution.
Solution Approach 2:
The lateral connecting rods act as intermediary elements between the primary structure and the wing, transferring forces and torques that would otherwise require a wider primary structure. These intermediaries enable force distribution without compromising the aerodynamic profile of the main mast.
3Length of stationary object
If forward wing attachments are positioned closer together to reduce width, then the structure becomes more compact, but the forces induced by couples increase
Solution Approach 1:
Lateral connecting rods serve as intermediary force transfer elements that relieve the forward wing attachments from bearing the full burden of couple forces. By providing alternative force pathways through the lateral rods, the system reduces the concentrated forces on the forward attachments even when they are positioned close together.
Solution Approach 2:
The force management function is segmented across multiple elements: forward wing attachments handle vertical forces, while lateral connecting rods and intermediate attachments share the burden of couple forces. This segmentation allows compact positioning of forward attachments without creating excessive localized forces.
Data Source
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AI summary
The invention relates to an aircraft comprising at least one wing attachment system that connects a wing (54) and a primary structure (62) of a mast and includes: - at least first and second wing attachments configured to provide at least partial load transfer and torque distribution, positioned at the upper spar (64.1) of the primary structure (62), - at least one lateral connecting rod (76) extending between first and second ends (76.1, 76.2) connected respectively to the primary structure (62) and the wing (54), the second end (76.2) being spaced at least in the horizontal transverse direction (Y) and/or the vertical transverse direction (Z) relative to the primary structure (62). According to this arrangement, it is possible to reduce the width of the primary structure (62) without increasing the stresses at the first and second wing attachments.