Foldable Rotor Blade Assembly With Synchronized Gear Hinges
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Solution Overview
Problem
Traditional drone propeller structures are either too complex with many parts, increasing costs, or too simple, failing to allow for efficient folding and storage, which compromises portability and risk of damage.
Innovation Solution
A foldable wing assembly with a synchronous transmission gear system, comprising a pair of opposing wing members and a gear assembly with support brackets and hinge members, allowing the wings to be simultaneously deployed and stowed, utilizing meshed gear teeth for synchronized movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a simple propeller structure is used, then the manufacturing cost is reduced, but the ability to fold and store the blades efficiently is lost
Solution Approach 1:
The propeller blade is designed with a hinge joint that allows it to rotate between a deployed position (for flight operation) and a folded position (for storage and transport). This dynamic capability enables the blade to adapt its configuration based on operational requirements, resolving the contradiction between simple structure and folding capability.
Solution Approach 2:
The propeller assembly is divided into separable components: the blade, the hinge mechanism, and the mounting structure. This segmentation allows the blade to be independently folded at the hinge while the rest of the structure remains stable, enabling efficient storage without requiring a completely complex redesign of the entire propeller system.
2Adaptability or versatility
If a complex propeller structure is used, then the folding and storage capability is improved, but the manufacturing cost and number of parts increase
Solution Approach 1:
The hinge joint incorporates a spring mechanism that provides automatic return force, eliminating the need for additional actuators or complex control systems. The spring enables the blade to automatically return to its neutral or folded position, reducing the number of parts while maintaining full folding capability.
Solution Approach 2:
The spring-loaded hinge mechanism is self-actuating, using the blade's own weight and the spring's stored energy to drive the folding and unfolding motions. This self-service mechanism eliminates the need for external motors, sensors, or control systems, significantly reducing part count while preserving adaptability.
3Stability of the object's composition
If the propeller blades are made fixed, then the structural integrity is maintained, but the portability and compact storage are compromised
Solution Approach 1:
The hinge joint is designed with a rigid connection when in the deployed position, maintaining structural integrity during flight. When folded, the hinge allows compact positioning without compromising the strength of the connection points. This dynamic rigidity-flexibility transition resolves the contradiction between fixed structure and compact storage.
Solution Approach 2:
The propeller blade is designed to fold parallel to the fuselage body, nesting within the overall aircraft envelope. This nesting arrangement minimizes the increased volume required for storage while maintaining the structural integrity of the blade and hinge assembly during both deployed and folded states.
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
Enhances the portability of multirotor drones by enabling efficient folding and deployment of wings, reducing the risk of damage and improving user experience through a compact storage solution.
Implementation Method 1
Each hinge member includes a set of gear teeth extending outwardly from an arcuate radially outer surface and coupled in a meshed arrangement with a corresponding set of gear teeth of an opposing hinge member such that a movement of one hinge member causes a synchronous movement of the other hinge member.
Data Source
AI summary
An unmanned aerial vehicle includes a fuselage body, a foldable wing assembly and a gear assembly. The foldable wing assembly, including a pair of opposing wing members, is coupled to the fuselage body and positionable in a stowed position and a deployed position. The gear assembly positions the wing members in a stowed position and a deployed position and include a support bracket assembly and a pair of opposing hinge members. The support bracket assembly is coupled to the fuselage body and including first and second support brackets forming a cavity therebetween and a pair of opposing hinge members. The pair of opposing hinge members are pivotably coupled to the support bracket assembly and positioned within the cavity. Each hinge member is coupled to a corresponding wing member and includes a set of gear teeth extending outwardly from an arcuate radially outer surface and coupled in a meshed arrangement.