VTOL Propulsion Ducted Fan Transition Mechanism
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Solution Overview
Problem
Developing a propulsion system for VTOL aircraft that can efficiently transition from vertical hover to horizontal flight and back, while being compact and reliable, has proven challenging, especially for radio-controlled models, as previous designs struggled to achieve smooth and controlled transitions.
Innovation Solution
A dual inline ducted fan design with turbine dynamics, featuring a compressor modified to generate a dense air mass, thrust vectoring, and adjustable nozzles, is used to achieve vertical flight and control, with a sealed casing and integrated components like pressure rings, valves, and vortices generators to enhance airflow and directional thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a ducted fan design is used for VTOL aircraft, then vertical flight capability is achieved, but transition smoothness and control stability deteriorate
Solution Approach 1:
The patent applies dynamics by making the ducted fan assembly rotatable to change the direction of thrust. The fan can rotate between vertical orientation for hover/vertical flight and horizontal orientation for forward flight, enabling smooth transition between flight modes while maintaining control stability through controlled rotation mechanics
Solution Approach 2:
The patent introduces a rotational dimension to the ducted fan assembly, allowing it to pivot between vertical and horizontal axes. This dimensional change enables the propulsion system to adapt from vertical thrust generation to horizontal thrust generation, resolving the contradiction between vertical flight capability and transition smoothness
2Adaptability or versatility
If twin rotatable externally mounted ducted-fan engines are used, then transitory flight is achieved, but aircraft compactness and internal mounting capability deteriorate
Solution Approach 1:
The patent merges the two separate ducted fan assemblies into a single integrated unit that rotates together as one structure. This consolidation reduces the overall volume required for mounting while maintaining the transitory flight capability, allowing the combined assembly to be internally mounted within the aircraft fuselage
Solution Approach 2:
The single rotatable ducted fan assembly performs multiple functions: it provides vertical thrust for hover, horizontal thrust for forward flight, and can be positioned in intermediate angles for transition phases. This multi-functionality replaces the need for two separate engines, reducing aircraft volume while maintaining versatility
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
The system enables reliable and efficient vertical takeoff, hover, and transition to forward flight, maintaining control and stability through adjustable thrust direction, allowing for precise maneuvering and landing, while being adaptable to various scales and sizes.
Implementation Method 1
a compressor modified to manipulate and generate a large dense air mass to provide steady and reliable thrust for flight
Implementation Method 2
The two ducted fans are configured to generate a dense air mass that can be angled downwardly for vertical flight or hover and can be angled backwards for forward flight
Implementation Method 3
The entire assembly is sealed air tight to create a de-facto pressure chamber. The thrust generated by the fans is forced through the casing assembly and enhanced
Implementation Method 4
Natural and artificially induced vacuums are augmented by pressure rings, valves, vortices generators and adjustable fins, flaps, and strakes
Implementation Method 5
Natural and artificially induced vacuums are augmented by pressure rings, valves, vortices generators
Data Source
AI summary
An aircraft, such as a radio controlled aircraft, capable of vertical take-off and landing. The aircraft has a compressor in a fuselage that contains an interconnected first and second fans driven by a motor. An intake provides air to the first fan, while a bypass duct directs airflow to the second fan. Air flow from the first fan to the second fan is controlled by a valve, which is operated in tandem with doors in the bypass duct. Nozzles direct air flow out of the compressor in a selected one of a vertical or non-vertical direction for conventional flight or for hover. Hover tubes are provided to adjust the aircraft in pitch, yaw and roll. The hover tubes operate simultaneously with conventional flight controls.