Rotating Wing and Rotor Assemblies for VTOL Flight Transitions

Solution Overview

Problem

Existing hybrid VTOL aircraft/UAVs face inefficiencies in transitioning between vertical and horizontal flight modes due to mechanically complex folding/swivelling systems that increase weight and are cumbersome, especially in adverse weather conditions.

Innovation Solution

An aeronautical vehicle with a wing assembly and rotor assembly that can rotate independently or coupled about pivot axes, allowing for efficient transitions between flight modes through a drive system, reducing structural complexity and weight.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If mechanically complex folding/swivelling systems are used to transition between flight modes, then the aircraft can transition between vertical and horizontal flight, but the weight of the aeronautical vehicle increases

Engineering Contradiction:

Improvetransition capability between flight modesVSAvoidvehicle weight

Core Design Contradiction:

Adaptability or versatilityVSWeight of moving object

Solution Approach 1:

The aircraft is divided into separate functional modules: a fixed wing assembly and an independent rotor assembly mounted on a rotor support. This segmentation allows each component to perform its function without requiring complex mechanical transformations, thereby reducing overall system weight while maintaining transition capability between flight modes.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The rotor support structure serves multiple functions: it mounts the rotor assembly, provides structural support during both vertical and horizontal flight, and enables rotation to transition between flight modes. This multi-functionality eliminates the need for separate mechanical systems for each function, reducing weight and complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Adaptability or versatility

If mechanically complex folding/swivelling systems are used to transition between flight modes, then the aircraft can transition between vertical and horizontal flight, but the device complexity increases

Engineering Contradiction:

Improvetransition capability between flight modesVSAvoidmechanical system complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The aircraft is divided into separate functional modules: a fixed wing assembly and an independent rotor assembly mounted on a rotor support. This segmentation allows each component to perform its function without requiring complex mechanical transformations, thereby reducing overall system weight while maintaining transition capability between flight modes.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The rotor support is rigidly coupled to the wing assembly, merging the support structure with the wing into a single integrated unit. This combination simplifies the mechanical system by eliminating separate support structures and reducing the number of moving parts required for transition between flight modes.

Inventive Principle:

Principle #5Merging (Combining)

3Device complexity

If a fixed configuration with wing and rotors is used, then the structure is simple, but the aircraft cannot perform optimally in either vertical or horizontal flight due to air flow disturbances

Engineering Contradiction:

Improvestructural simplicityVSAvoidflight performance in adverse weather

Core Design Contradiction:

Device complexityVSReliability

Solution Approach 1:

The rotor support is configured to rotate about a vertical pivot axis, enabling the rotor assembly to change its position dynamically. During transition, the rotor support rotates to position the rotors optimally relative to the wing, minimizing air flow disturbances and improving performance in both vertical and horizontal flight modes while maintaining structural simplicity.

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS20250296675A1Aeronautical vehicle and method of transitioning between flight modes for an aeronautical vehicle

Publication Date: 2025.09.25 TECH UNIV DELFT

AI summary

An aeronautical vehicle performs horizontal flight and/or vertical flight, and has a fuselage, a wing assembly having a first wing part and a second wing part rigidly coupled to one another, a rotor assembly, a horizontal thruster, and an attitude control system. The wing assembly is arranged rotatably with respect to the fuselage to rotate about a vertical pivot axis between a stow position and an active position. The rotor assembly includes two vertical thrust rotors arranged on a rotor support rotatably with respect to the fuselage to rotate the rotor assembly between a stow position and an active position. In a horizontal flight mode the wing assembly is in the active position and the rotor assembly is in the stow position, and in a vertical flight mode the wing assembly is in the stow position and the rotor assembly is in the active position.