Internal Wing Control Surface Linkage for UAVs
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Solution Overview
Problem
Unmanned aerial vehicles (UAVs) face challenges in quickly and reliably converting between stowed and deployed configurations of control surfaces, such as fins and wings, which complicates storage and portability due to the need for multiple control surfaces and potential interference with weight distribution and aerodynamics.
Innovation Solution
An internal wing control surface linkage system is developed, featuring an actuator arm rotating within an airfoil body's cavity, a linking arm with a hinged end pivotally coupled to the actuator arm, and a spherical bearing for swivelly coupling, allowing the control surface to deflect relative to the airfoil body without damaging the linkage or fin during configuration changes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If control surfaces are deployed externally for proper UAV operation, then flight control capability is improved, but storage and portability are worsened due to increased size and complexity
Solution Approach 1:
The control surface linkage system is nested within the hollow cavity of the airfoil body. The actuator arm, linking arm with tube and rod, and spherical bearing all fit inside the airfoil's internal space, allowing the control surfaces to be stored compactly within the wing structure itself rather than extending externally.
Solution Approach 2:
The linkage system utilizes the third dimension by placing components in the depth of the airfoil body's hollow cavity. The actuator arm rotates within the cavity, and the linking mechanism extends and retracts along the longitudinal axis of the airfoil, effectively using internal volume to achieve compact storage.
2Strength
If heavy components are placed externally for structural support, then structural strength is improved, but weight distribution and aerodynamics are worsened
Solution Approach 1:
The heavy actuator and linkage components are extracted from external mounting positions and placed inside the airfoil body's hollow cavity. This removes the source of weight distribution problems and aerodynamic drag from the external surfaces, while the airfoil structure itself provides the necessary structural support.
Solution Approach 2:
The linkage system components are merged with the airfoil body structure by utilizing its hollow cavity as the housing. The actuator arm, linking arm, and spherical bearing are integrated within the airfoil's internal volume, combining the structural function of the airfoil with the mechanical function of the linkage system.
3Speed
If control surfaces are quickly converted between stowed and deployed configurations, then operational speed is improved, but reliability is worsened due to increased stress on linkage components
Solution Approach 1:
The spherical bearing provides a cushioning effect by allowing smooth rotational movement of the linking arm as it transitions between positions. This bearing absorbs and distributes the stresses that occur during rapid configuration changes, preventing damage to the linkage components while enabling quick deployment and stowing.
Solution Approach 2:
The linkage system is designed with dynamic components that can adapt during motion: the actuator arm rotates about a fixed axis, the spherical bearing allows multi-directional rotation, and the rod slides within the tube. These dynamic elements enable rapid configuration changes while distributing mechanical stresses throughout the system to maintain reliability.
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 solution enables efficient conversion between stowed and deployed configurations without stressing the control surface linkage or fin, improving weight distribution and aerodynamics by keeping heavy components inside the fuselage and reducing external protuberances, thus enhancing the UAV's portability and flight characteristics.
Implementation Method 1
A spherical bearing mountable in the cavity and swivelly coupling the linking arm. Deflection of a tip of the control surface relative to the airfoil body is achieved, via a spherical bearing providing a fixed swivel pivot which swivels the linking arm
Data Source
AI summary
An internal wing control surface linkage system comprising: an actuator arm configured to rotate around a first rotation axis within an airfoil body. A linking arm is mounted within the airfoil body. The linking arm comprises a linking tube and a linkage rod slideably received within the linking tube. The linking tube comprises a hinged end pivotally coupled to the actuator arm about a first pivot axis parallel to the first rotation axis to cause deflection of a control surface coupled to the airfoil body during rotation of the actuator arm. The linkage rod comprising a hinged end coupled to a clevis about a second pivot axis of the control surface. A spherical bearing swivelly coupling the linking arm and providing a fixed swivel pivot which swivels the linking arm, as the linking tube simultaneously slides within the spherical bearing and, in combination, the rod simultaneously slides within the linking tube.