Aircraft Fairing Panel Seal With Rigid Stop for Gap Variation
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Solution Overview
Problem
Current aircraft fairing sealing methods are time-consuming, and the hardened seals often fail to consistently fill gaps between panels and the secondary structure, are not removable without damage, and do not accommodate dimensional variations due to vibration and aerodynamic phenomena.
Innovation Solution
An aircraft fairing design featuring a compressible seal with a rigid stop and extra thickness, where the compressible seal is supported by the fairing panel and has a compression ratio of 10-85%, allowing it to adapt to varying gaps and maintain a seal without complete compression, thus ensuring a waterproof seal without the need for polymerization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If polymerization sealing method is used to obtain a hardened seal, then the seal provides structural integrity, but the sealing process becomes time-consuming and the panel cannot be removed without damaging the seal
Solution Approach 1:
The sealing system is segmented into a removable panel portion and a fixed structure portion, allowing the panel to be detached and reattached. The seal itself is segmented into compressible sealing elements that can deform to accommodate panel removal and reinstallation, eliminating the need for permanent polymerized bonds.
Solution Approach 2:
The seal material parameters are changed from rigid polymerized state to compressible elastic state. This allows the seal to provide sufficient sealing pressure through elastic deformation while remaining removable and reusable, resolving the contradiction between seal integrity and removability.
2Reliability
If a rigid hardened seal is used, then the seal provides consistent sealing, but it cannot accommodate dimensional variations due to vibration and aerodynamic phenomena
Solution Approach 1:
The sealing system transitions from a static rigid seal to a dynamic compressible seal that can adapt its shape and volume. The seal elements are designed to compress and deform dynamically in response to dimensional variations caused by vibration and aerodynamic forces, maintaining reliable sealing under varying conditions.
Solution Approach 2:
The seal utilizes flexible compressible material that can deform to accommodate changes in the gap between the panel and structure. This flexible sealing approach maintains consistent sealing pressure while adapting to dimensional variations, resolving the contradiction between seal consistency and adaptability.
3Adaptability or versatility
If the seal is designed to be fully compressible, then it can accommodate all dimensional variations, but it cannot maintain sufficient sealing pressure
Solution Approach 1:
The seal is designed with partial compressibility rather than full compressibility. The compressible portion accommodates dimensional variations while the uncompressed portion maintains sufficient sealing pressure. This partial action approach resolves the contradiction between adaptability and sealing strength.
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 significantly reduces the time required for sealing, allows for the removal and reinstallation of panels without damaging the seal, and accommodates dimensional changes due to vibrations and aerodynamic forces, ensuring a consistent and effective waterproof seal.
Implementation Method 1
the seal being a compressible seal having a compression ratio, the stop and the compressible seal being configured such that the compression ratio of the compressible seal is less than or equal to 90%
Data Source
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AI summary
The invention relates to an aircraft fairing comprising at least one structure (22), at least one fairing panel (24), at least one fastener (26) connecting the fairing panel (24) and the structure (22), and at least one compressible seal (36) interposed between first and second bearing zones attached respectively to the fairing panel (24) and the structure (22). The fairing panel (24) includes at least one rigid stop (34) positioned in the first bearing zone, the stop (34) and the compressible seal (36) being configured such that the compression ratio of the compressible seal (36) is less than or equal to 90%. The invention also relates to an aircraft comprising at least such a fairing.