Aircraft Wing Hold-Down Arrangement for High-Lift Device
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Solution Overview
Problem
High-lift devices on aircraft wings, such as slats, detach from the wing surface during deformation due to inadequate mounting, leading to reduced aerodynamic performance and increased weight due to the need for robust construction to withstand deformation loads.
Innovation Solution
A hold-down arrangement with a load-limited elastically deformable biasing means and a rigid hold-down element is used, allowing the high-lift device to maintain contact with the wing surface during normal flight conditions but releasing contact during extreme loads, reducing the need for excessive robustness and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the high-lift device is mounted using only two supports spaced apart in the spanwise direction, then the device allows spanwise displacement relative to the wing, but the trailing edge detaches from the wing surface when the wing deforms
Solution Approach 1:
A hold-down arrangement acts as an intermediary element between the high-lift device and the wing surface. This intermediary component actively maintains contact between the trailing edge and the wing during spanwise deformation, resolving the contradiction by providing additional support without restricting the fundamental displacement capability of the two-support mounting system
2Strength
If the high-lift device is constructed to be robust enough to withstand deformation loads, then the device maintains structural integrity, but the weight increases excessively
Solution Approach 1:
The hold-down arrangement serves as a mediator that protects the high-lift device from excessive deformation loads by maintaining proper contact with the wing surface. This allows the high-lift device to be constructed with reduced robustness and lower weight, while the hold-down mechanism absorbs the stress of maintaining contact during wing deformation
3Reliability
If the hold-down arrangement maintains constant contact during all flight conditions, then aerodynamic performance is optimized, but the structural loads and weight increase
Solution Approach 1:
The hold-down arrangement employs dynamic characteristics with elastically deformable components that adapt their stiffness and contact force based on flight conditions. During normal flight, the elastic elements maintain gentle contact for aerodynamic performance, while during extreme maneuvers, the dynamic response allows controlled detachment or increased compliance, reducing the need for overly robust and heavy construction
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
This solution ensures the high-lift device remains in contact with the wing surface during regular flight, improving aerodynamics while allowing reduced construction and weight during normal conditions, and mitigating detachment during extreme conditions.
Implementation Method 1
one of the first hold-down element and the second hold-down element is a load-limited hold-down element comprising an elastically deformable biasing means
Data Source
AI summary
A wing for an aircraft is disclosed including a fixed wing, a high-lift device and a hold-down arrangement arranged between two supports of the high lift device having a first hold-down element attached to the high-lift device and a second hold-down element attached to the fixed wing. The first hold-down element contacts the second hold-down element when the high-lift device is in a retracted position in which it prevents a trailing edge of the high-lift device from detaching from an upper surface of the fixed wing when the fixed wing bends in the spanwise direction. One of the hold-down elements is a load-limited hold-down element which comprises a biasing means. When the load transmitted through the hold-down arrangement exceeds an operational threshold, elastic deformation of the biasing element results in the hold-down arrangement no longer preventing the trailing edge high-lift device from detaching from the upper surface of the fixed wing.