Aircraft Wing Flap With Decoupled Linear-Rotational Motion
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Solution Overview
Problem
Existing trailing edge high lift assemblies for aircraft wings are limited in their ability to dynamically adjust wing shape in response to flight conditions, primarily due to coupled linear and rotational movements of the flap, restricting optimal lift, drag, and structural loading optimization.
Innovation Solution
A decoupled linear and rotational movement mechanism for the flap, utilizing independent actuators to allow independent linear and rotational adjustments, enabling a wider range of wing configurations through a connection assembly with a guide rail and carriage system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the flap is movably mounted using a coupled linear and rotational mechanism (e.g., carriage on guide rail with rotating drive arm), then the flap can be moved between retracted and extended positions, but the movement path is restricted to a single predefined path, limiting wing shape adjustment freedom
Solution Approach 1:
The connection assembly is segmented into two independent functional components: a linear movement mechanism (carriage on guide rail) and a rotational movement mechanism (hinge on lever element). This segmentation allows the flap to achieve both linear and rotational degrees of freedom independently, enabling adjustment to multiple different wing shapes rather than being constrained to a single predefined path.
Solution Approach 2:
The patent employs a counteracting mechanism where the coupled linear and rotational movements are designed to balance each other, allowing the flap to move along a complex trajectory that optimizes wing shape for different flight conditions while maintaining structural efficiency.
2Productivity
If a single predefined movement path is used for the flap, then the connection assembly structure is simpler, but the ability to optimize lift, drag, and structural loading during different flight stages is reduced
Solution Approach 1:
The connection assembly is designed as a dynamic system with two independently controllable actuators that can adjust the flap's position and orientation in real-time. This dynamic capability allows the wing shape to be optimized for different flight stages (take-off, landing, cruise) by varying both the linear position and rotational angle of the flap, rather than following a fixed movement path.
Solution Approach 2:
The patent changes the movement parameters from a single predefined trajectory to two independent parameters: linear displacement along the guide rail and rotational angle at the hinge. This parameter expansion enables continuous adjustment of wing shape to optimize aerodynamic performance across different flight conditions.
3Adaptability or versatility
If the flap is fixedly mounted on a rotating lever, then the structure is simpler, but the flap cannot be moved in a linear manner, limiting wing area and curvature adjustment
Solution Approach 1:
The connection assembly is segmented into two independent functional components: a linear movement mechanism (carriage on guide rail) and a rotational movement mechanism (hinge on lever element). This segmentation allows the flap to achieve both linear and rotational degrees of freedom independently, enabling adjustment to multiple different wing shapes rather than being constrained to a single predefined path.
Solution Approach 2:
The patent adds a linear movement dimension to the traditional rotational flap mechanism. By combining linear displacement along the guide rail with rotational movement at the hinge, the flap gains an additional degree of freedom, transforming the movement from one-dimensional (rotational only) to two-dimensional (linear + rotational), thereby expanding the range of achievable wing configurations.
Data Source
AI summary
A wing for an aircraft. The wing includes a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing. The trailing edge high lift assembly includes a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly is configured such that the flap is movable relative to the main wing in a linear and/or rotational manner. The connection assembly is configured such that the flap is movable relative to the main wing in a decoupled linear and rotational manner.