Hybrid Trailing-Edge Control Surface for Low-Drag Yaw Authority
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Solution Overview
Problem
Existing aircraft control surfaces, particularly those with double hinges, create significant drag due to mechanical blisters and are complex to implement on large commercial aircraft, requiring significant deflections and deformations.
Innovation Solution
A hybrid control surface configuration featuring a forward control surface rotatably attached to a support structure via a pivot axis and a rearward control surface with a deformable skin, actuated by independent first and second driving means to achieve double curvature, reducing the need for multiple hinges and enhancing aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If double hinged control surfaces are used to maximize yaw power, then control authority is improved, but drag increases significantly due to mechanical blisters
Solution Approach 1:
The control surface is divided into two separate hinges: a first hinge for actuating the control surface relative to the lifting surface, and a second hinge for actuating a portion of the control surface relative to the first control surface. This segmentation allows each hinge to be optimized for its specific function, reducing the need for large mechanical blisters that create drag.
Solution Approach 2:
The patent introduces a hierarchical actuation system where the first hinge provides primary actuation and the second hinge provides secondary actuation. This multi-dimensional control approach maximizes yaw power through coordinated movement of multiple segments rather than relying on a single large-hinge configuration that would increase drag.
2Loss of energy
If morphing trailing edges are implemented to reduce actuation loads and minimize drag, then aerodynamic efficiency is improved, but system complexity increases significantly for commercial aircraft
Solution Approach 1:
The patent employs dynamic control surfaces that can change their aerodynamic characteristics during flight. The control surfaces are capable of varying their deflection angles and effective area through the two-hinge mechanism, allowing the system to adapt to different flight conditions and reduce actuation loads without requiring complex morphing structures.
Solution Approach 2:
The system changes aerodynamic parameters by adjusting the deflection angles of the control surface and its portions through the two-hinge mechanism. This allows the control surface to optimize its performance across different flight regimes, reducing actuation loads by operating in high-lift configurations when needed while maintaining simplicity through conventional hinge mechanisms rather than complex morphing structures.
3Device complexity
If conventional single hinge control surfaces are used, then structural simplicity is maintained, but control authority and yaw power are insufficient
Solution Approach 1:
The control surface is segmented into multiple actuated portions through two hinges, allowing each segment to contribute to the overall control authority. This segmentation provides enhanced yaw power compared to a single hinge system while maintaining relative structural simplicity by using conventional hinge mechanisms rather than complex morphing structures.
Solution Approach 2:
The patent combines the actuation functions of two hinges working in coordination to achieve enhanced control authority. The first hinge actuates the control surface relative to the lifting surface, while the second hinge actuates a portion of the control surface, and their combined effect provides superior yaw power while maintaining structural simplicity through the use of conventional mechanical hinge mechanisms.
Data Source
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AI summary
The present invention belongs to the field of aircraft movable parts, namely to the configuration of aerodynamic surfaces. More in particular, it relates to the architecture of an aerodynamic surface (1) comprising two control surfaces (3, 4) towards its trailing edge adapted to modify the lift and drag characteristics of said aerodynamic surface. The invention relates to a hybrid control surface comprising a forward control surface (3) and a rearward control surface (4) and the movement actuation of these control surfaces to enable lifting surface curvature.