Foldable Propeller Blade Locking Mechanism Against Forward Folding
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Solution Overview
Problem
Current unmanned aerial vehicles (UAVs) with compact configurations are limited in flight range, endurance, and payload capacity.
Innovation Solution
The UAVs feature deployable components such as telescoping wings, deployable stabilizers, and foldable propeller blades, allowing for multiple configurations including compact, deployed, and expanded arrangements, enhancing aerodynamic efficiency and payload capacity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the UAV uses a compact configuration with stowed wings and stabilizers, then the space and deployment options are improved, but the flight range, endurance, and payload capacity are limited
Solution Approach 1:
The patent implements dynamically reconfigurable airframe components including telescoping wings that can extend from a compact stowed position to an expanded flight position, and deployable stabilizers that transition from a retracted state to a deployed state. These dynamic transformations allow the UAV to optimize its volume for transport and its aerodynamic surface area for flight, resolving the contradiction between compactness and flight endurance.
Solution Approach 2:
The UAV airframe is segmented into modular components: the wing is divided into telescoping sections that can extend independently, and the stabilizer is segmented into deployable elements. This segmentation enables selective deployment of components based on operational needs, allowing the UAV to achieve both compact storage and expanded flight capability without requiring complete structural redesign.
2Adaptability or versatility
If the UAV uses a compact configuration with stowed components, then the deployment options are improved, but the aerodynamic efficiency is reduced
Solution Approach 1:
The patent employs dynamic reconfiguration mechanisms that allow the UAV to transition between compact and expanded configurations based on operational phase. During transport, the telescoping wing retracts to minimize cross-section, while during flight, it extends to maximize aerodynamic surface area, thereby maintaining high aerodynamic efficiency across different deployment scenarios.
Solution Approach 2:
The compact configuration is prepared in advance for efficient transport and rapid deployment. The telescoping wing and deployable stabilizer are pre-positioned in a stowed state that enables quick transition to flight configuration, allowing the UAV to maintain both deployment versatility and aerodynamic efficiency by having the optimal configuration ready for each operational phase.
3Length of moving object
If the UAV uses deployable components such as telescoping wings and deployable stabilizers, then the flight range and payload capacity are improved, but the device complexity increases
Solution Approach 1:
The wing is segmented into telescoping sections with standardized coupling mechanisms, and the stabilizer is divided into modular deployable elements. This segmentation allows each component to be independently controlled and positioned, simplifying the overall control architecture while enabling extended wingspan and improved aerodynamic performance.
Solution Approach 2:
The telescoping wing mechanism serves multiple functions: it extends the wingspan for improved aerodynamic efficiency, provides structural support for payload capacity, and enables compact storage for deployment. The deployable stabilizer similarly provides both flight stability and aerodynamic surface area. This multi-functionality reduces the need for separate systems, thereby managing device complexity while achieving multiple performance goals.
Data Source
AI summary
An unmanned aerial vehicle with deployable components (UAVDC) may comprise a foldable propeller blade with a locking mechanism. Foldable propeller blades may have a stowed configuration and a deployed configuration relative to the UAVDC, and the foldable propeller blades may pivot about a hinge to move between configurations. In the deployed configuration, the foldable propellor may experience forward folding forces acting upon it. The locking mechanism may lock the foldable propeller blade in the deployed configuration. The locking mechanism may keep the foldable propeller locked into place to prevent forward folding tendency.