Slat Inboard Buffering Structure for Aircraft Noise Reduction
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Solution Overview
Problem
Existing leading-edge high-lift devices on aircraft wings generate excessive noise from the slat inboard end portion and supporting mechanism, which conventional noise reduction methods like cove fillers and serrations fail to address effectively.
Innovation Solution
A leading-edge high-lift device with a slat main body and a buffering portion, featuring a flexible material or fence member at the inboard end to modify airflow and reduce pressure fluctuations, and a porous layer to lower flow velocity, thereby inhibiting airflow separation and interference with the supporting mechanism.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If conventional slat designs are used, then the aircraft can achieve sufficient lift during low-speed flight, but excessive noise is generated from the slat inboard end portion and supporting mechanism
Solution Approach 1:
The patent applies local quality by introducing a buffering portion with specific geometric features (curved surface, porous structure, or flexible material) only at the slat inboard end portion where noise is generated. This localized modification allows the slat to maintain its overall lift-generating function while specifically addressing the noise problem at the problematic inboard region through tailored flow control features
2Object-generated harmful factors
If cove fillers or serrations are added to the slat lower surface, then noise from the reverse flow region in the cove is reduced, but noise from the slat inboard end portion and supporting mechanism remains unaddressed
Solution Approach 1:
The patent segments the noise reduction approach by distinguishing between two distinct noise sources: (1) noise from the reverse flow region in the cove, addressed by conventional cove fillers or serrations, and (2) noise from the slat inboard end portion and supporting mechanism, addressed by the novel buffering portion. This segmentation allows each region to be treated with appropriate flow control features, expanding overall noise reduction coverage
3Object-generated harmful factors
If the slat is designed with a buffering portion to reduce noise, then noise from the inboard end portion is reduced, but the device complexity increases
Solution Approach 1:
The patent employs flexible shells and thin films by using a buffering portion that can be implemented as a flexible membrane or thin-walled structure. This buffering portion is deformable and can adapt to the aerodynamic loads while providing noise reduction through its geometric configuration (curved surface, porous structure, or flexible material), thereby reducing noise without significantly increasing structural complexity
Solution Approach 2:
The patent utilizes porous materials by incorporating a buffering portion with a porous structure at the slat inboard end portion. The porous configuration allows controlled flow through the buffering portion, reducing pressure fluctuations and noise generation while maintaining structural integrity. This approach achieves noise reduction with minimal added complexity compared to solid structures
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 proposed solution significantly reduces noise generated from the slat inboard end portion and supporting mechanism by minimizing airflow separation and interference, leading to a quieter aircraft operation.
Implementation Method 1
reduces pressure fluctuations in airflow on the inboard end surface or the inboard-side surface of the cove portion
Implementation Method 2
noise comes from turbulence in reverse flow regions formed at concaves (coves)
Implementation Method 3
The structure may include a flexible material that is deformed so as to be capable of entering a gap between the slat main body and the main wing during retraction
Implementation Method 4
A leading-edge high-lift device with a slat main body and a buffering portion, featuring a flexible material or fence member at the inboard end to modify airflow and reduce pressure fluctuations, and a porous layer to lower flow velocity
Data Source
AI summary
A leading-edge high-lift device is deployable and retractable from/into a fixed leading edge of a main wing of an aircraft and includes a slat main body and a buffering portion. The slat main body includes a leading edge portion, a trailing edge portion, a cusp portion formed at a lower edge of the leading edge portion, a cove portion formed between the cusp portion and the trailing edge portion, and an inboard end surface that is formed between the leading edge portion and the cove portion and is positioned on a fuselage side of the aircraft. The buffering portion is provided at an inboard end portion of the slat main body including the inboard end surface and an inboard-side surface of the cove portion and reduces pressure fluctuations in airflow on the inboard end surface or the inboard-side surface of the cove portion.