Aircraft Lifting Surface Sliding Actuation Mechanism
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Solution Overview
Problem
Conventional aircraft lifting surface actuation systems require heavy support structures and fairings outside the aerodynamic profile, leading to weight increase and drag penalties, while struggling to efficiently increase camber and chord simultaneously.
Innovation Solution
An actuation system utilizing a sliding mechanism with a guide track and complementary element allows the movable part to slide relative to the stationary structure, generating both translation and rotation, thereby increasing camber and chord without intermediate supports or fairings outside the aerodynamic profile.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional actuation systems with heavy support structures and fairings outside the aerodynamic profile are used, then the control surfaces can be actuated, but weight increases and aerodynamic drag is penalized
Solution Approach 1:
The invention extracts the actuation mechanism from the conventional configuration with external fairings and support structures. The sliding system is integrated within the aerodynamic profile itself, eliminating the need for heavy external fairings while maintaining control surface actuation functionality.
Solution Approach 2:
The invention changes the dimensional arrangement by moving the rotation axis inside the aerodynamic profile rather than outside. This dimensional repositioning allows the control surface to be actuated through the thickness of the profile, eliminating external fairings and reducing drag.
2Reliability
If multiple actuators and support structures are located along the span of the wing, then control surfaces can be actuated, but device complexity and weight increase
Solution Approach 1:
The invention merges the actuation function into a single integrated sliding system that combines translation and rotation capabilities. This eliminates the need for multiple separate actuators and support structures distributed along the wing span, reducing overall system complexity.
Solution Approach 2:
The sliding system performs multiple functions simultaneously: it provides both translation and rotation of the control surface, acts as the support structure, and maintains aerodynamic cleanliness. This multi-functionality reduces the number of components needed compared to conventional systems.
3Device complexity
If control surfaces are located only at the trailing edge, then the actuation system is simpler, but lift efficiency is reduced compared to leading and trailing edge control surfaces
Solution Approach 1:
The invention enables dynamic control surface configuration where the movable part can achieve both camber change and chord extension. This dynamic capability allows the system to optimize lift efficiency similar to having both leading and trailing edge control surfaces, while maintaining a simpler single-location actuation system.
Data Source
Figure 1
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AI summary
Aircraft lifting surface (2) having a span direction, the lifting surface (2) comprising: - a stationary part (3), - a movable part (1), movable with respect to the stationary part (3) and comprising an end (4) in the span direction, - an actuation system configured to actuate the movable part (1) with respect to the stationary part (3). The actuation system comprising a sliding system joined to: - the end (4) of the movable part (1), and - configured to be joined to a stationary structure (6) of the aircraft, said stationary structure (6) being: • located adjacent in the span direction to the end (4) of the movable part (1), and • connected with the stationary part (3) of the lifting surface, so that the sliding system allows the movable part (1) to slide with respect to the stationary structure (6).