Deformable Leading Edge Section for Aircraft Wing
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Solution Overview
Problem
Current leading edge devices on aircraft, such as slats, generate noise during deployment and extension, which affects aircraft noise levels and lift efficiency, as they create air recirculation and gaps that increase noise and reduce lift when extended for takeoff and landing.
Innovation Solution
A flight control surface system comprising a leading edge section, a trailing section, and a deformable section, where the deformable section connects the two and changes shape to reduce air recirculation and noise, using shape memory alloys and actuators to move the leading edge section between deployed and undeployed positions, eliminating gaps and optimizing airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a retractable slat is extended to increase lift during takeoff and landing, then the stalling speed is reduced and lift is increased, but noise is generated by air passing over the slat and the gap between the slat and the wing
Solution Approach 1:
The patent extracts and eliminates the gap between the slat and the wing by using a flexible panel that conforms to the wing surface. This removes the source of noise generation (air passing through the gap) while preserving the lift-enhancing function of the extended slat during takeoff and landing operations.
Solution Approach 2:
The patent employs a flexible panel (thin film structure) that can adapt its shape to eliminate gaps between the slat and wing surface. This flexible structure maintains aerodynamic smoothness when the slat is extended, preventing noise-generating turbulence while allowing the slat to remain in its lift-augmenting position.
2Object-generated harmful factors
If a leading edge flap is used to reduce noise, then noise is reduced compared to an extendable slat, but the amount of lift that can be generated is reduced
Solution Approach 1:
The patent implements a dynamic system where the slat can extend and retract, and the flexible panel dynamically adapts its shape. When the slat is retracted, the flexible panel maintains a smooth surface for low noise. When the slat is extended, the flexible panel conforms to the new geometry, eliminating gaps and maintaining low noise while preserving the full lift-generating capability of the extended slat position.
Solution Approach 2:
The patent changes the physical state and geometry of the flexible panel based on the slat position. The flexible panel transitions from one configuration (when slat is retracted) to another configuration (when slat is extended), allowing the system to achieve both low noise and high lift performance at different operational phases without compromise.
3Force
If a slat is extended to increase lift, then lift is increased for takeoff and landing, but air recirculation occurs that increases noise and reduces efficiency
Solution Approach 1:
The patent removes the air recirculation problem by eliminating the gap between the slat and wing using the flexible panel. This extraction of the gap eliminates the recirculation zone, thereby reducing energy loss and improving the efficiency of the lift-generating mechanism during takeoff and landing operations.
Solution Approach 2:
The patent converts the potential harm of air recirculation into a benefit by using the flexible panel to guide airflow smoothly. The flexible panel's ability to conform to the slat geometry transforms what would be a harmful recirculation zone into a beneficial smooth airflow pattern that enhances lift while minimizing energy loss.
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 system reduces noise and stalling speed by minimizing air recirculation and maintaining lift efficiency during normal flight, while reducing noise pollution and enhancing aircraft performance.
Implementation Method 1
The flexible panel is comprised of a shape memory alloy. The flexible panel has an original shape and is connected to the skin panel and the leading edge section.
Implementation Method 2
The deformable section has an original shape that is configured to deform when the leading edge section moves into an undeployed position. The original shape is configured to return substantially to the original shape when the leading edge section extends into a deployed position.
Data Source
AI summary
A method and apparatus for managing a flight control surface system. A leading edge section on a wing of an aircraft is extended into a deployed position. A deformable section connects the leading edge section to a trailing section. The deformable section changes from a deformed shape to an original shape when the leading edge section is moved into the deployed position. The leading edge section on the wing is moved from the deployed position to an undeployed position. The deformable section changes to the deformed shape inside of the wing.