Rotatable UAV Control Surface Assembly for Stowed Storage
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Solution Overview
Problem
Unmanned aerial vehicles (UAVs) face challenges in quickly and reliably converting control surfaces between stowed and deployed configurations, which complicates storage and portability due to the need for multiple fins and the interference of heavy actuator components with weight distribution and aerodynamics.
Innovation Solution
A control surface assembly featuring a fin rotatably coupled to the fuselage with a control surface member and linkage actuated by an actuator within the fuselage, allowing the control surface member to rotate in the deployed configuration and move without rotating in the stowed configuration, using a mechanical linkage that maintains functionality without stressing the linkage or fin.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple fins with control surfaces are used to ensure proper UAV operation, then flight capability is improved, but storage and portability are worsened due to complexity
Solution Approach 1:
The control surface assembly is segmented into modular components: a fin, a control surface member rotatably coupled to the fin, and a control surface linkage. This segmentation allows the control surface to be independently adjusted relative to the fin, enabling the system to adapt between flight and storage configurations without requiring multiple complete fin assemblies.
Solution Approach 2:
The control surface member is designed to be dynamically adjustable through rotation relative to the fin via the control surface linkage. An actuator enables the control surface to transition between deployed and stowed positions, providing dynamic adaptability that resolves the contradiction between maintaining flight capability and reducing storage complexity.
2Ease of operation
If control surface linkage is actuated in stowed configuration, then deployment control is improved, but damage to linkage or fin occurs
Solution Approach 1:
The system incorporates a detection mechanism that determines whether the fin is in the stowed or deployed configuration before allowing actuator operation. This preliminary detection prevents the control surface linkage from being actuated when the fin is stowed, thereby avoiding damage to the linkage or fin while still enabling full deployment control when the fin is properly positioned.
Solution Approach 2:
A control system acts as an intermediary between the actuator and the control surface linkage. This intermediary monitors the fin configuration state and selectively enables or disables actuator operation, preventing harmful actuation in the stowed configuration while maintaining full operational control when the fin is deployed.
3Weight of moving object
If actuator is disposed in the fuselage, then weight distribution and aerodynamics are improved, but control surface actuation complexity increases
Solution Approach 1:
The control surface linkage is designed with different functional characteristics for different fin configurations. When the fin is deployed, the linkage is configured to rotate the control surface member in response to actuator actuation. When the fin is stowed, the linkage is configured to move without rotating the control surface member. This local adaptation of linkage behavior eliminates the need for complex conditional control mechanisms.
Solution Approach 2:
The control surface linkage serves multiple functions depending on the fin configuration: it transmits actuator motion to rotate the control surface member when the fin is deployed, and it accommodates actuator motion without rotating the control surface when the fin is stowed. This multi-functionality allows the actuator to be disposed in the fuselage for optimal weight distribution while maintaining simple actuation control.
Data Source
AI summary
A control surface assembly for an unmanned aerial vehicle (UAV) is disclosed. The control surface assembly has a fin configured to be rotatably coupled to a fuselage of the UAV, with a control surface member rotatably coupled to the fin. A control surface linkage is configured to be coupled between the control surface member and an actuator disposed in the fuselage. The fin is rotatable with respect to the fuselage between a stowed configuration and a deployed configuration. In the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin, when the actuator actuates the control surface linkage. In the stowed configuration, however, the control surface linkage is configured to move with respect to the fin without rotating the control surface member, when the actuator actuates the control surface linkage.