Aircraft Wing Flap Support Beam for Lower Drag
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Solution Overview
Problem
Existing aircraft wings with support elements require fairings to guide flaps, which increase drag due to their external placement and complexity.
Innovation Solution
Employing an elongate support beam with guide bearings, such as roller bearings, to movably connect the flap to the main wing, minimizing the need for fairings and optimizing the wing's aerodynamic profile.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a support element in the form of a carriage rolling or sliding along a rail is used, then the flap can be moved between retracted and extended positions, but the rail extends outside of the main wing contour and requires a fairing that increases drag
Solution Approach 1:
The invention extracts the support element from the conventional carriage-rail configuration and replaces it with a support beam that is integrated into the wing structure. The support beam is mounted within the wing contour, eliminating the need for external fairings and reducing drag while still enabling flap movement between retracted and extended positions.
Solution Approach 2:
The invention changes the spatial arrangement by positioning the support beam longitudinally within the wing rather than using an external rail. The support beam extends from the trailing edge toward the leading edge, utilizing the internal space of the wing structure to guide flap movement without protruding externally.
2Ease of operation
If a rotating arm mounted outside the main wing contour is used, then the flap can be moved between retracted and extended positions, but a fairing is required which increases drag
Solution Approach 1:
The invention removes the external rotating arm and its associated fairing by integrating the support function directly into the wing structure through the support beam. The support beam is positioned within the wing contour, eliminating the need for external fairings that increase drag.
3Reliability
If a fairing is used to cover the support element, then the structure is protected and guided, but the fairing increases drag and complicates the wing structure
Solution Approach 1:
The invention merges the support element with the wing structure by integrating the support beam within the wing contour. This integration eliminates the need for separate fairings, as the support beam itself is positioned within the aerodynamic profile of the wing, thereby reducing drag while maintaining structural guidance.
4Reliability
If a fairing is used to cover the support element, then the structure is protected and guided, but the fairing increases weight
Solution Approach 1:
The invention combines the support function with the existing wing structure by positioning the support beam within the wing contour. This eliminates the need for additional fairing structures, thereby reducing the overall weight of the wing assembly while maintaining reliable support element guidance.
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
Reduces drag and simplifies the wing's structure by eliminating or minimizing fairings, enhancing efficiency and reducing weight.
Implementation Method 1
The guide bearing comprises a roller bearing including at least a first roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion and/or at the front end of the support beam
Data Source
AI summary
A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly having a flap, and a connection assembly movably connecting 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 includes a support element that is mounted to the flap and that is movably mounted to the main wing, such that the support element is movable relative to the main wing along a predefined path between a stowed position and a deployed position. The support element is formed as an elongate support beam that extends along a beam longitudinal axis between a front end and a rear end and has an intermediate portion between the front and rear ends.