Aircraft Hinge Fairing with Bell-Shaped Leading Edge Profile
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Solution Overview
Problem
Folding wing tip devices on aircraft cause undesirable lift loss and drag due to the use of conventional fairing shapes at the junction between the fixed wing and wing tip device, which are not aerodynamically efficient.
Innovation Solution
A fairing with a front portion blended into the leading edge of the fixed wing and wing tip device, featuring a bell-shaped profile and continuous curvature, which minimizes discontinuities and reduces lift loss by seamlessly integrating with the wing surface, covering the hinge arrangement without extending beyond the leading edge.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional fairing shapes are used at the junction between fixed wing and wing tip device, then the hinge arrangement is covered, but lift loss and drag increase due to aerodynamic discontinuities
Solution Approach 1:
The fairing employs a bell-shaped profile with continuous curvature that smoothly blends into the leading edge of the fixed wing and wing tip device. This curved geometry eliminates abrupt transitions and aerodynamic discontinuities, reducing flow separation and stagnation points while maintaining coverage of the hinge arrangement, thereby decreasing lift loss and drag.
Solution Approach 2:
The fairing design changes the geometric parameters of the junction area by extending the bell-shaped profile rearwardly from the leading edge with continuous curvature. This parameter modification creates a smooth aerodynamic transition zone that reduces discontinuities and improves airflow characteristics, eliminating the energy losses associated with conventional fairing shapes.
2Loss of energy
If the fairing is blended into the leading edge with continuous curvature, then aerodynamic efficiency is improved, but the manufacturing complexity increases
Solution Approach 1:
The fairing is divided into distinct functional portions: a front portion that blends into the leading edge with continuous curvature, and a rear portion that extends rearwardly. This segmentation allows each portion to be optimized for its specific aerodynamic function while simplifying the overall manufacturing process by breaking down the complex geometry into manageable segments.
Solution Approach 2:
The fairing applies different geometric characteristics to different locations: the front portion features continuous curvature blending for optimal leading edge flow, while the rear portion has a different profile optimized for rearward flow management. This local differentiation of geometric quality achieves high aerodynamic efficiency without requiring complex geometry throughout the entire fairing structure.
Data Source
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AI summary
The invention relates to aircraft with wing tip devices, for example, folding wing tips. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a front portion blended into and extending rearwardly from the leading edge of the fixed wing and the wing tip device.