Leading Edge Surface for Lift Dumping and Stall Margin
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Solution Overview
Problem
Existing aircraft wing designs face challenges in reducing complexity and space occupation of flight control surfaces without compromising their functionality, particularly in situations with space constraints.
Innovation Solution
A moveable leading edge device is mounted closer to the leading edge of the wing, rotatably mounted and configured to rotate between configurations, allowing it to be retracted into the wing profile or extend into the airflow to disrupt airflow, thereby providing lift generation and dumping capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If traditional flight control surfaces are arranged on the wing, then lift generation and control functions are achieved, but device complexity and space occupation increase
Solution Approach 1:
The patent combines multiple flight control surfaces (leading edge device and trailing edge flap) into a single integrated system. The leading edge device is positioned forward of the front spar, allowing it to work in conjunction with the trailing edge flap to achieve both lift generation and dump functions, thereby reducing overall device complexity while maintaining functionality.
Solution Approach 2:
The leading edge device is designed to perform multiple functions: it can generate lift when deployed forward of the leading edge, dump lift when retracted behind the leading edge, and control airflow separation. This multi-functionality reduces the need for separate dedicated control surfaces, simplifying the overall system.
2Reliability
If multiple flight control surfaces are arranged on the wing, then control functionality is improved, but space occupation within the wing increases
Solution Approach 1:
The leading edge device is positioned in the spanwise direction forward of the front spar, utilizing space that would otherwise be unused. This dimensional repositioning allows the device to occupy space outside the traditional wing internal volume, reducing the space occupation within the wing structure while maintaining control functionality.
3Productivity
If leading edge device is mounted closer to the leading edge, then airflow disruption capability is improved, but structural complexity increases
Solution Approach 1:
The wing structure is segmented into distinct zones: the leading edge device is mounted forward of the front spar, which itself is forward of the main wing box. This segmentation allows the leading edge device to be positioned optimally for airflow disruption while being structurally supported by the front spar, reducing the complexity of integrating the device into the wing structure.
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 complexity and space requirements of flight control surfaces by utilizing a single device for both lift generation and dumping functions, enhancing lift coefficient and stall angle of attack, while minimizing weight and complexity.
Implementation Method 1
The oncoming airflow is disrupted as it travels around the wing profile as it enters the cavity through the void in the lower surface near the leading edge
Implementation Method 2
In the third configuration, the leading edge device increases the wing camber and the lift coefficient of the wing which increases the stall angle of attack
Data Source
Figure 1~2
Figure 3~4
Figure 5A~5B
AI summary
An aircraft wing with a moveable leading edge device (22) mounted towards the leading edge of the wing. The leading edge device (22) is moveable between a first configuration and a second configuration. In the first configuration, the leading edge device (22) is substantially flush with the low pressure surface. In the second configuration, the surface of the leading edge device (22) is retracted into the wing profile. The second configuration creates a void (C) in the lower surface of the wing which modifies the airflow over the surfaces. The oncoming airflow can enter the void (C). In the second configuration, the leading edge device (22) reduces the lift on the wing, acting to reduce the lift induced strain on the wing during high speed flight or to help manoeuvre the wing. The leading edge device (22) may also be configured to move into a third configuration. In the third configuration, the leading edge device (22) protrudes from the surface and modifies the airflow over the wing. In the third configuration, the leading edge device (22) generates lift on the wing, acting to help improve an angle of attack to prevent stalling on the wing.