Rotational Connector for Aircraft Wing Trailing Edge Camber
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Solution Overview
Problem
Existing aircraft wing trailing edge section assemblies for high aspect ratio wings face challenges in reliability and space constraints, particularly in high aspect ratio wings where torsionally flexible wings require movable trailing edge devices near the tip to achieve roll responsiveness and wing tip load alleviation, and existing mechanisms like sliding actuators are not suitable due to space limitations and potential 'aileron reversal' effects.
Innovation Solution
A compact mechanism involving a rotationally mounted connector member between upper and lower skin structures, allowing simultaneous movement and changing the camber of the trailing edge section, which reduces the need for control surface hinges, aerodynamic seals, and provides additional torsional stiffness, suitable for high aspect ratio wings and foldable wing tips.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If sliding actuators are used to change the contour of upper and lower surfaces of a trailing edge section, then the camber can be changed, but the mechanism takes up a lot of space within the wing section and reliability may be compromised
Solution Approach 1:
Instead of using sliding actuators that move linearly along the trailing edge, the patent inverts the approach by using a rotationally mounted connector member that pivots to simultaneously move both upper and lower skin structures. This rotational mechanism achieves the same camber change function while occupying significantly less space within the wing section and eliminating the need for long sliding actuator strokes.
Solution Approach 2:
The patent merges the actuation of upper and lower skin structures into a single rotational movement of the connector member. By connecting both skin structures to the same rotational pivot point, the system achieves coordinated movement of both surfaces simultaneously, reducing the number of separate actuation mechanisms needed and minimizing the overall space requirement within the wing section.
2Loss of energy
If high aspect ratio wings are used to reduce induced drag and increase fuel burn efficiency, then fuel efficiency is improved, but the wings are torsionally flexible and require movable trailing edge devices located very near the tip with little space for actuation mechanisms
Solution Approach 1:
The patent applies the inversion principle by replacing traditional linear sliding actuators with a rotational pivot mechanism. This allows the trailing edge device to be located very near the wing tip with minimal space for actuation, as the rotational connector requires only a small pivot point rather than the extended space needed for sliding mechanisms to achieve the same camber adjustment range.
Solution Approach 2:
The patent employs dynamic skin structures that can flex and change shape in response to the rotational movement of the connector. The upper and lower skin structures are designed with tailored panel stiffness to allow bending and flexing, enabling the trailing edge to achieve the required camber changes dynamically without requiring rigid, space-intensive actuation mechanisms.
3Speed
If movable trailing edge devices are located very near the tip of high aspect ratio wings to achieve roll responsiveness, then roll responsiveness is improved, but the control surfaces need to be large enough to overcome aileron reversal effects
Solution Approach 1:
By inverting the actuation mechanism from linear sliding to rotational pivoting, the patent enables the trailing edge device to be positioned extremely close to the wing tip. This proximity to the tip maximizes the leverage and effectiveness of the control surface, allowing for smaller control surface areas to achieve the same roll responsiveness, thereby preventing aileron reversal effects with reduced 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
This solution enables smooth and continuous camber change, reduces twisting moments on the primary structure, eliminates the need for control surface hinges and aerodynamic seals, and provides a compact, reliable actuation mechanism suitable for high aspect ratio wings, preventing 'aileron reversal' effects and maintaining a clean aerodynamic profile.
Implementation Method 1
a rotationally mounted connector member connected between the first and second portions, such that rotational movement of the connector member causes simultaneous movement of both first and second portions
Data Source
AI summary
An aircraft wing trailing edge section assembly is disclosed having an upper skin structure providing an upper external aerodynamic trailing edge surface, a lower skin structure providing a lower external aerodynamic trailing edge surface, and a movement mechanism including a first portion attached to an internal surface of the upper skin structure, a second portion attached to an internal surface of the lower skin structure, and a rotationally mounted connector member connected between the first and second portions, such that rotational movement of the connector member causes simultaneous movement of both first and second portions and therefore both upper and lower skin structures, such that the camber of the trailing edge section is changed. An aircraft wing section assembly, an aircraft and methods of operating an aircraft are disclosed.