Aircraft High-Lift Slats and Flaps Transition Control
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Solution Overview
Problem
The transition from a smooth wing configuration to a high-lift configuration during an aircraft's approach phase is prolonged due to slow extension of slats and flaps, requiring either a long approach or powerful, bulky actuation means.
Innovation Solution
An intermediate configuration with partially extended flaps is introduced, allowing slats to be extended while flaps are partially extended and then retracted as speed increases, speeding up the transition to the second high-lift configuration without using ultrapowerful actuation means.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the extension of the slats and the extension of the flaps are slow, then the approach level must be longer, but this causes nuisance in air traffic
Solution Approach 1:
The patent segments the flap extension process into two distinct phases: first extending the slats to achieve a first configuration with very slight high lift, then extending the flaps to achieve a second configuration with average high lift. This segmentation allows each component to be extended separately and at optimized speeds, avoiding the need for a single prolonged extension process while preventing the need for overly powerful actuation systems.
2Loss of time
If the extension of the slats and the extension of the flaps are rapid, then the approach level can be shorter, but this requires very powerful, bulky and heavy hydraulic and/or electrical actuation means
Solution Approach 1:
The patent divides the high-lift configuration into two sequential stages: first configuration with extended slats only, and second configuration with both extended slats and flaps. This segmentation allows the use of moderate-speed actuation means for each component separately, avoiding the need for a single rapid extension system that would require powerful, bulky, and heavy actuators.
Solution Approach 2:
The patent introduces dynamic control of the wing configuration by automatically transitioning between first and second configurations based on aircraft speed thresholds. The control system monitors speed and automatically extends or retracts the flaps relative to the slats, enabling adaptive adjustment of the approach level duration without requiring manual pilot intervention or overly powerful fixed-speed actuators.
3Productivity
If the extension of the slats and the extension of the flaps are rapid, then the transition is faster, but this requires ultrapowerful, bulky and heavy actuation means
Solution Approach 1:
The patent segments the transition process into distinct phases: extension of slats to first configuration, then extension of flaps to second configuration. This segmentation allows each actuation system to operate at moderate speeds with simple, lightweight actuators, rather than requiring a single rapid-action ultrapowerful actuation system, thereby reducing device complexity while maintaining transition efficiency.
Solution Approach 2:
The patent implements dynamic control that automatically manages the transition between configurations based on real-time speed monitoring. The control system activates flap extension only when appropriate speed thresholds are met, enabling flexible and efficient transition management without complex mechanical actuation systems or ultrapowerful devices.
Data Source
AI summary
According to the invention, high lift leading-edge slats (13) and high lift flaps (14) are simultaneously deployed, when the speed of the aircraft is equal to and less than an AES threshold.