Foldable VTOL Aircraft Propulsion Hinges
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Solution Overview
Problem
Current VTOL UAVs face challenges in occupying a small footprint during storage and maintaining stability, leading to reduced efficiency due to the need for surface actuators and increased energy usage for stability control, which affects thrust capability.
Innovation Solution
A foldable VTOL aircraft design with rotatably coupled propulsion assemblies and motor support arms using hinges, allowing for compact storage and eliminating the need for surface actuators, while maintaining stability through differential thrust and torque control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of stationary object
If VTOL UAVs use fixed propulsion assemblies, then stability is maintained, but footprint during storage increases and energy usage for stability control increases
Solution Approach 1:
The propulsion assemblies are made dynamically movable through hinges, allowing them to transition between extended flight positions and retracted storage positions. This dynamic configuration enables the aircraft to adapt its footprint for storage while maintaining stability during flight through differential thrust control, eliminating the need for surface actuators and reducing energy consumption.
Solution Approach 2:
The propulsion system is segmented into independently controllable assemblies that can be positioned differently relative to the main body. This segmentation allows each propulsion assembly to be optimized for its function while enabling compact storage configuration, and provides multiple thrust vectors for stability control without requiring additional surface actuators.
2Length of moving object
If propulsion assemblies are extended for flight, then span and thrust capability increase, but footprint during storage increases
Solution Approach 1:
The motor support arms are designed with hinge joints that allow them to dynamically change position between extended and retracted configurations. During flight, the arms extend to provide full span and thrust capability; during storage, they retract to minimize footprint, achieving both requirements through a single adaptable structure.
3Stability of the object's composition
If surface actuators are added for stability control, then stability improves, but device complexity and energy usage increase
Solution Approach 1:
The patent extracts and eliminates the need for surface actuators by using the propulsion assemblies themselves for stability control. The propulsion assemblies are positioned and controlled to provide both thrust and stability functions, removing the separate stability control system and reducing overall device complexity while maintaining longitudinal and directional stability.
Solution Approach 2:
The propulsion assemblies are designed to perform multiple functions: providing thrust for flight and simultaneously providing stability control through differential thrust and torque. This multi-functionality eliminates the need for separate surface actuators, reducing device complexity and energy usage while maintaining stability.
Data Source
AI summary
One embodiment is an aircraft including a main body, a plurality of propulsion assemblies, and a plurality of hinges, wherein each of the plurality of propulsion assemblies is rotatably coupled to the main body using a hinge from the plurality of hinges. In an example, the aircraft includes four motor support arms and each motor support arm rotatably couples a specific propulsion assembly to a specific corresponding hinge on the main body of the aircraft and increases a span of the aircraft when the aircraft is in the flight configuration and reduces the footprint of the aircraft when the aircraft is in a storage configuration.