Wing-Integrated Leading-Edge Droop Linkage for Compact Actuation
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Solution Overview
Problem
Conventional leading-edge actuators for aircraft wings are large, heavy, and inefficient, consuming space and power, making them difficult to integrate and reducing aircraft efficiency.
Innovation Solution
A leading-edge droop actuation system with a compact actuator disposed within the wing, coupled to an aerodynamic surface via a linkage system, using a bell crank and hinge arms to move between retracted and drooped positions, providing linear motion along the wing length.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional leading-edge actuators are used to deploy aerodynamic surfaces, then the aerodynamic surface can be deployed to control lift/drag characteristics, but the actuator becomes large, heavy, and consumes significant space and power
Solution Approach 1:
The actuator system is divided into multiple segments: a compact linear actuator, a bell crank mechanism, and hinge arms. This segmentation allows the actuator to be much smaller while the bell crank and hinge arms provide the necessary mechanical advantage to deploy the aerodynamic surface, resolving the contradiction between small actuator size and reliable deployment capability.
Solution Approach 2:
The bell crank mechanism acts as an intermediary between the compact linear actuator and the aerodynamic surface. It converts the linear motion from the small actuator into the appropriate rotational motion for the hinge arms, enabling the large aerodynamic surface to be deployed by a much smaller actuator.
2Reliability
If conventional leading-edge actuators are used, then the aerodynamic surface can be deployed, but the actuator consumes significant power and reduces aircraft efficiency
Solution Approach 1:
By segmenting the actuation system into a compact linear actuator and passive mechanical linkages (bell crank, hinge arms), the system reduces power consumption. The mechanical linkages provide mechanical advantage that reduces the power required from the actuator itself, while still achieving reliable deployment of the aerodynamic surface.
Solution Approach 2:
The bell crank mechanism serves as an intermediary that amplifies the force and reduces the power requirement for the actuator. It converts the small amount of power from the compact actuator into the sufficient force needed to deploy the aerodynamic surface against aerodynamic loads.
3Reliability
If large actuators are used to overcome aerodynamic forces, then the aerodynamic surface can be deployed reliably, but the actuator is difficult to integrate into the aircraft
Solution Approach 1:
The actuation system is segmented into a compact linear actuator that can be easily integrated into the wing structure, and separate mechanical linkages (bell crank, hinge arms) that provide the necessary deployment force. This segmentation makes integration much easier compared to integrating a single large actuator.
Solution Approach 2:
The bell crank mechanism acts as an intermediary that bridges the gap between the compact actuator and the aerodynamic surface. It allows the small actuator to control the deployment of the larger aerodynamic surface through mechanical advantage, making integration feasible without requiring a large actuator.
4Reliability
If conventional actuators are used, then the aerodynamic surface can be deployed, but the weight of the actuator reduces aircraft efficiency
Solution Approach 1:
By segmenting the actuation system into a compact linear actuator and passive mechanical linkages, the overall weight is significantly reduced compared to using a single large actuator. The compact actuator weighs much less, and the mechanical linkages add minimal weight, thereby improving aircraft efficiency while maintaining reliable deployment capability.
Solution Approach 2:
The bell crank mechanism serves as a lightweight intermediary that provides mechanical advantage. It allows the compact, lightweight actuator to effectively deploy the aerodynamic surface without requiring a heavy actuator, thus improving aircraft efficiency while maintaining deployment reliability.
Data Source
AI summary
An aircraft includes a wing and a leading-edge aerodynamic surface coupled to the wing. An actuator is disposed within the wing and coupled to the leading-edge aerodynamic surface via a linkage system. Two or more hinge systems are coupled to the leading-edge aerodynamic surface and configured to rotate about a fixed axis internal to the wing to move the leading-edge aerodynamic surface between a retracted position and a drooped position.