Aircraft Control Surface Actuation Mechanism for Thin Wing Drag Reduction
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Solution Overview
Problem
The challenge of installing geared rotary actuators in thin wing aircraft configurations is exacerbated by reduced cross-sectional area, leading to increased drag and offsetting the benefits of thin wing designs, as conventional actuators housed within the wing face space constraints and detrimental drag impacts.
Innovation Solution
The actuator system is reconfigured to be primarily housed within the aircraft flight control element, utilizing a drive shaft, first and second rotary actuator elements, and a spar connection to achieve relative movement between the wing and control surfaces, allowing for translation and rotation of the control surfaces while minimizing components within the wing, thus creating an air gap and improving aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional actuators are housed within the wing, then control surface actuation is achieved, but drag increases and wing space is reduced
Solution Approach 1:
The actuator system is extracted from the wing interior and repositioned to be primarily housed within the aircraft flight control element. This extraction eliminates the need for drop hinges and internal wing mounting structures, thereby reducing drag while maintaining actuation functionality.
Solution Approach 2:
The actuator system transitions from a three-dimensional interior wing mounting to a configuration that utilizes the space between the wing and control surface. This dimensional repositioning creates an air gap that reduces drag while providing adequate space for actuator operation.
2Object-affected harmful factors
If wing cross-sectional area is reduced for thin wing design, then aerodynamic efficiency improves, but actuator installation space is reduced
Solution Approach 1:
The actuator system is repositioned to utilize the interstitial space between the wing and control surface, transitioning from interior wing mounting to an external configuration. This dimensional change provides adequate actuator space without compromising thin wing aerodynamics.
Solution Approach 2:
The actuator system is divided into components that can be distributed within the flight control element and connected to the wing via spar connections. This segmentation allows the actuator to function effectively in the reduced space available in thin wing configurations.
3Device complexity
If drop hinges are used for control surface attachment, then simple attachment is achieved, but drag increases significantly
Solution Approach 1:
The drop hinge attachment mechanism is extracted and replaced with a spar connection system that attaches the actuator to the wing spar. This elimination of drop hinges removes the source of significant drag while maintaining simple attachment functionality through the spar connection.
4Object-affected harmful factors
If actuator components are minimized within the wing, then drag is reduced, but control mechanism simplicity is reduced
Solution Approach 1:
The actuator system merges the drive shaft, rotary actuator elements, and control surface attachment into an integrated assembly that is housed within the flight control element. This merging reduces the number of separate components within the wing while maintaining full actuation functionality through the unified system.
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 configuration enhances aerodynamics by eliminating drop hinges, reduces weight through simplified mechanisms, and optimizes wing space for other components like fuel storage, while maintaining efficient control surface operation.
Implementation Method 1
a first rotary actuator element operably coupled to the drive shaft and configured to be driven in a first direction about the drive shaft, a second rotary actuator element positioned adjacent the first rotary actuator element and operably coupled to the drive shaft and configured to be driven in a second direction about the drive shaft, the second direction being a counter-rotation relative to the first direction
Implementation Method 2
a spar connection configured to pivotably connect the first rotary actuator element to the spar at a fixed coupler
Data Source
AI summary
Assemblies having a first structure, a second structure movable relative to the first structure, and an actuator system arranged therebetween and configured to control relative movement therebetween. The actuator system includes a drive shaft, a first element configured to be driven in a first direction, and a second element configured to be driven in a second direction. A spar is fixedly connected to the first structure and a spar connection pivotably connects the first element to the spar at a fixed coupler. The drive shaft, the first element, and the second element are housed within the second structure. Rotation of the second element causes a translation motion of the drive shaft away from the first structure and rotation of the first element about the fixed coupler such that the second structure is translated and rotated relative to the first structure.