eVTOL Folding Mechanism with Segmented Beams
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Solution Overview
Problem
Existing eVTOL aircraft folding mechanisms are heavy, cumbersome, and require complex fixtures, leading to high interface loads and wear on connector elements, making them difficult to transport and store efficiently.
Innovation Solution
The design features a fuselage with rotatably attached longitudinal and crossbeams, eliminating the central hub and using ring connectors for stability, allowing for folding without disassembling components and using quick release fasteners for easy transport, with load paths distributed via these beams to reduce stress on the fuselage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a central hub with folding mechanisms is used to attach lifting units, then the aircraft can be folded for transport, but the mechanism becomes heavy and increases interface loads on connector elements
Solution Approach 1:
The aircraft structure is divided into separate longitudinal beams and crossbeams that can be independently folded, eliminating the need for a heavy central hub. Each beam is attached to the fuselage independently, allowing the lifting units to be distributed across multiple separate structural elements rather than concentrated at a single central point.
Solution Approach 2:
The central hub is completely removed from the design. Instead of having all folding mechanisms converge at a central point, the patent extracts the hub function and distributes the folding capability across multiple beam-to-fuselage attachment points, thereby eliminating the weight and complexity of a central hub structure.
2Adaptability or versatility
If existing folding mechanisms are used, then the aircraft can be disassembled for storage, but complex fixtures are required and handling becomes cumbersome
Solution Approach 1:
The structure is segmented into modular beams that can be independently folded and secured. Each beam can be folded separately without requiring complex ground fixtures, as the folding action is distributed across multiple simple attachment points rather than requiring a single complex central folding mechanism.
Solution Approach 2:
Instead of using complex fixtures on the ground to facilitate folding, the patent inverts the approach by designing the beams themselves to be inherently foldable through simple attachment mechanisms. The folding capability is built into the structure rather than requiring external fixing equipment.
3Adaptability or versatility
If heavy additional devices are added for folding mechanisms, then the aircraft can be folded, but the flying range and payload capacity are reduced
Solution Approach 1:
The folding function is distributed across multiple lightweight beam attachments rather than requiring a single heavy central mechanism. This segmentation allows the use of simpler, lighter attachment devices at each beam-to-fuselage connection point, reducing the total weight added for folding capability.
Solution Approach 2:
The heavy central hub and its associated heavy-duty folding mechanisms are extracted from the design. By removing this weight, the aircraft gains additional payload capacity and extended flying range while retaining folding capability through the lighter distributed beam attachment system.
4Strength
If the aircraft structure uses a central hub for load transfer, then structural integrity is maintained, but high interface loads cause wear and tear on connector elements
Solution Approach 1:
The load transfer path is segmented into multiple independent beam-to-fuselage attachment points rather than concentrating all loads at a single central hub. This distributes the interface loads across multiple connectors, reducing wear and tear on individual connector elements while maintaining overall structural integrity.
Solution Approach 2:
The central hub, which concentrates all structural loads and causes high interface wear, is extracted from the design. The load transfer function is redistributed to multiple separate beam attachments, eliminating the wear problem associated with a single high-load central connector while preserving structural strength.
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 design enhances durability and stability while reducing weight, enabling easier handling and transportation of eVTOL aircraft, allowing for container shipping and single-person operation without the need for additional tools or major component removal.
Implementation Method 1
said longitudinal beams are rotatably attached to said fuselage by means of at least one respective first pivot joint devised for pivoting said longitudinal beams around a respective first pivot axis to a pivoted position; and wherein said crossbeam is rotatably attached to said fuselage, preferably by means of at least one second pivot joint, for pivoting said crossbeam around a second pivot axis to a pivoted position
Data Source
AI summary
An aircraft with folding mechanism, the aircraft including a fuselage, optionally a payload and/or landing gear attached to the fuselage, at least two longitudinal beams attached to the fuselage that preferably extend parallel to each other and parallel to a first aircraft axis, with lifting units attached to each of the longitudinal beams. At least one crossbeam is attached to the fuselage, and preferably extending parallel to a second aircraft axis and at right angles with respect to the longitudinal beams, with lifting units attached to the crossbeam. The longitudinal beams are rotatably attached to the fuselage by at least one respective first pivot joint configured for pivoting the longitudinal beams around a respective first pivot axis to a pivoted position. The crossbeam is rotatably attached to the fuselage, preferably by at least one second pivot joint, for pivoting the crossbeam around a second pivot axis to a pivoted position.