Aircraft Wing Flap Gap Closure for Morphing Aerodynamics
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Solution Overview
Problem
Existing wings fail to optimize wing area, curvature, and angle of attack during flight without negatively affecting aerodynamic performance.
Innovation Solution
A wing design with a movable flap that includes a passive gap closing device, allowing for a second retracted position with reduced chord length and a gap closure mechanism to minimize drag and structural loading, while maintaining optimal aerodynamic performance across various flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the flap is moved to extended positions to increase lift and reduce minimum air speed, then wing area and curvature are increased, but drag increases during cruise flight
Solution Approach 1:
The flap is designed to be dynamically adjustable between multiple positions (retracted, first extended, second extended) allowing the wing configuration to adapt to different flight conditions. This enables optimization of lift during takeoff/landing and minimization of drag during cruise flight
Solution Approach 2:
The wing geometry parameters (chord length, curvature, wing area) are changed by moving the flap between different positions. The gap closing device further modifies these parameters by opening or closing the gap between wing panels, thereby changing aerodynamic characteristics to match flight requirements
2Loss of energy
If the gap between wing panels is closed to reduce drag in retracted positions, then aerodynamic performance is improved, but airflow energyization along the flap surface is prevented
Solution Approach 1:
The gap closing device is dynamically controlled to open or close based on flap position. It remains closed during extended positions to enable airflow energyization, and opens during retracted positions to minimize drag, thereby adapting to different operational requirements
Solution Approach 2:
The gap closing device is positioned and configured in advance to automatically or controllably close the gap when the flap is in retracted positions, preventing harmful airflow leakage before it can negatively impact aerodynamic performance
3Loss of energy
If a second retracted position with reduced chord length is introduced to further reduce drag, then aerodynamic performance is improved, but the complexity of flap position control increases
Solution Approach 1:
The flap system is segmented into multiple discrete positions (retracted, first extended, second extended) with the gap closing device corresponding to each position. This segmentation allows independent optimization of each position while maintaining overall system manageability
Solution Approach 2:
The gap closing device acts as an intermediary element that couples the flap position with aerodynamic performance optimization. It mediates between the flap's geometric configuration and the airflow characteristics, enabling the second retracted position to achieve drag reduction without proportionally increasing control complexity
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 design reduces drag and structural loading by closing the gap between the wing panels in retracted positions and allowing airflow in extended positions, achieving optimized aerodynamic performance throughout the flight.
Implementation Method 1
a gap is present between a lower rear panel, preferably skin panel, of the main wing and a leading edge section of the flap to allow an air flow to pass between the flap and the main wing, in order to energize the air flow along the top surface of the flap
Data Source
Figure 1
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AI summary
Disclosed is a wing (3) for an aircraft (1), comprising a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5), the trailing edge high lift assembly (9) comprising a flap (11) and a connection assembly movably mounting the flap (11) to the main wing (5), such that the flap (11) is movable between at least one retracted position (12, 14) and at least one extended position (15), wherein in the at least one extended position (15) a gap (16) is present between a lower rear panel (17) of the main wing (5) and a leading edge section (19) of the flap (11), and wherein in the at least one retracted position (12, 14) the gap (16) is closed or minimized. The object of the invention, to provide a wing that might be used as a morphing wing capable of adjusting wing area, curvature, and angle of attack during the entire flight, while having optimized aerodynamic performance throughout all flap settings, is achieved in that the flap (11) is movable between at least one extended position (15), a first retracted position (12), and a second retracted position (14) where the flap (11) is moved beyond the first retracted position (12) in a forward direction (13), and the wing comprises a gap closing device (23) configured to close or minimize the gap (16) in both the first retracted position (12) and the second retracted position (14) of the flap (11), and to open the gap (16) in the at least one extended position (15) of the flap.