Rotor Deployment Linkage With Torsion Box Stiffness for eVTOL
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Solution Overview
Problem
Existing rotor assembly deployment mechanisms in vertical take-off and landing aircraft lack sufficient stiffness and strength, particularly during transitions between vertical and forward flight configurations, and often require complex gimbal systems for torque transfer.
Innovation Solution
A rotor assembly deployment mechanism utilizing a torsion box construction with a large-diameter primary pivot and rotary actuators, such as harmonic drives, to deploy and stow electric motors and propellers, providing enhanced stiffness and strength while eliminating the need for gimbal systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional deployment mechanisms are used, then the structure is simpler, but the stiffness and strength are insufficient during transitions between vertical and forward flight configurations
Solution Approach 1:
The patent employs a torsion box construction which utilizes composite material structures to achieve high stiffness and strength-to-weight ratio. The torsion box provides rigid structural support during rotor assembly deployment while maintaining lightweight characteristics essential for aerial vehicles.
Solution Approach 2:
The deployment mechanism is divided into modular components including bar linkages, rotary actuators, and pivot points. This segmentation allows each component to be optimized for specific functions while collectively providing the required structural integrity during configuration transitions.
2Stability of the object's composition
If traditional pivot designs are used, then the manufacturing is easier, but the stiffness during deployment is insufficient
Solution Approach 1:
The patent employs a large-diameter pivot design where the pivot diameter is significantly larger than the span of the pivot connection. This curved/spherical interface provides enhanced stiffness and stability during rotor assembly deployment while maintaining manufacturability through standard machining processes.
3Volume of moving object
If compact deployment is achieved, then the storage space is reduced, but the propellers may not clear the nacelle and wings effectively
Solution Approach 1:
The bar linkage mechanism utilizes multi-dimensional motion paths to deploy the rotor assembly outward and upward, allowing propellers to clear the nacelle and wings effectively while maintaining a compact stowed configuration during forward flight. The linkage system transforms limited space into effective deployment volume through geometric arrangement.
Data Source
AI summary
A rotor assembly deployment mechanism configured to deploy a rotor assembly of a vertical take-off and landing aircraft from a horizontal, forward thrust, position to a vertical, hover, position. The rotor assembly deployment mechanism is configured to deploy an electric motor and propeller together. The deployment mechanism provides significant stiffness and strength with the use of torsion box constructions. The deployment mechanism may utilize bar linkages wherein the primary linkage pivot is of a large diameter relative to the span of the pivot in order to provide significant stiffness. The deployment mechanism may utilize rotary actuators to drive the deployment and stowing of the rotor assembly.