Aircraft Fairing Flexible Joint Mass Reduction
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Solution Overview
Problem
Aircraft fairing hinges made of metallic materials are prone to corrosion and vibrations, leading to increased on-board mass due to their rigid structure.
Innovation Solution
A flexible joint articulation system comprising elastically deformable wings and a junction zone, where the wings form a single part with cutouts, reducing mass and allowing automatic return to a stable state, is used to connect fixed and movable panels, incorporating an L-shaped angle iron and a tongue mechanism for locking the movable panel in place.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a rigid metallic hinge structure is used to connect fixed and movable panels, then the structural strength and stability are improved, but the on-board mass increases and corrosion resistance deteriorates
Solution Approach 1:
The patent changes the physical state and material properties of the hinge from rigid metallic to flexible polymer material. This parameter change allows the hinge to maintain sufficient structural strength while dramatically reducing mass and eliminating corrosion issues. The flexible material can deform elastically under load while providing the necessary connection strength between panels.
Solution Approach 2:
The patent employs composite material construction for the flexible hinge, combining polymer materials with embedded reinforcement elements or layered structures. This composite approach ensures that the hinge achieves the required strength and stiffness characteristics while maintaining the low mass and corrosion resistance benefits of polymer-based materials.
2Stability of the object's composition
If a rigid metallic hinge structure is used to connect fixed and movable panels, then the structural stability is improved, but the corrosion resistance deteriorates
Solution Approach 1:
The patent fundamentally changes the material composition parameter from metallic to polymer-based flexible material. This eliminates the electrochemical corrosion mechanism that affects metallic hinges while maintaining structural stability through the elastic deformation capabilities and inherent stability of polymer materials in aerospace environments.
3Weight of moving object
If a flexible joint with cutouts is used to reduce mass, then the on-board mass is reduced, but the structural strength may deteriorate
Solution Approach 1:
The patent applies segmentation by introducing cutouts that divide the hinge structure into distinct sectors. These cutouts strategically remove material to reduce mass while the remaining structural sectors maintain load-bearing capabilities. The segmentation creates an optimized balance between mass reduction and structural integrity.
Solution Approach 2:
The patent applies local quality by concentrating material and structural reinforcement in specific critical areas of the hinge while removing material from non-critical regions through cutouts. This ensures that structural strength is maintained where loads are applied while achieving mass reduction in areas where material is less critical.
4Weight of moving object
If a flexible joint with cutouts is used to reduce mass, then the on-board mass is reduced, but the manufacturing complexity may increase
Solution Approach 1:
The patent merges multiple hinge components into a single integrated flexible joint structure with embedded cutouts. This monolithic construction eliminates the need for separate parts and assembly operations, actually simplifying manufacturing despite the complex geometry. The cutouts are incorporated into the mold or forming process rather than requiring post-manufacturing operations.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution reduces the mass of the joint and the overall aircraft mass while maintaining the movable panel in a stable closed position, enhancing aerodynamic efficiency and reducing corrosion risks.
Implementation Method 1
la zone de jonction est configurée pour se déformer de manière élastique
Implementation Method 2
la languette est configurée pour occuper un état de verrouillage dans lequel lʼextrémité libre coopère avec le premier aile et/ou la deuxième face de lʼL-angle, empêchant un basculement du panneau mobile depuis la position fermée vers la position ouverte
Data Source
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Figure 5~6
AI summary
The invention relates to an aircraft fairing comprising at least one hinge (52) connecting a fixed panel (44) and a movable panel (48), said hinge (52) having at least one first wing (54) connected to the fixed panel (44), at least one second wing (56) connected to the movable panel (48), and an elastically deformable junction zone (58) connecting the first and second wings (54, 56), the first and second wings (54, 56) and the junction zone (58) forming a single piece. Providing a one-piece hinge (52) reduces its mass and consequently the aircraft's onboard mass. The invention also relates to an aircraft comprising such a fairing.