Multi-mode Aerial Vehicle Tilt-Wing Tri-Ducted Fan Design
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Solution Overview
Problem
Current VTOL/STOL aerial vehicles face challenges in achieving a balance between vertical take-off and landing capabilities, speed, range, payload capacity, and operational efficiency, with issues such as high fuel consumption for hovering and limited range and safety concerns like rotor failures and ground resonance in helicopters.
Innovation Solution
A multi-mode aerial vehicle design incorporating a tilt-wing tri-ducted fan platform with dual counter-rotating rotors, Ogival Delta wings, and a WIG-effect bottom, allowing for vertical, short take-off and landing, and horizontal flight modes, while reducing complexity and increasing stability, maneuverability, and safety through a combination of fixed-wing, tilt-wing, and ducted fan configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a jet engine or turbo-fan engine is vectored downward to provide vertical lift in a nozzle-vectored fixed-wing VTOL/STOL aerial vehicle, then vertical take-off and landing capability is achieved, but fuel consumption increases significantly and horizontal flight time and range are reduced
Solution Approach 1:
The aerial vehicle divides the lifting function between multiple components: fixed wings provide primary lift during horizontal flight, while tilt wings with ducted fans provide vertical lift during VTOL operations. This segmentation allows each component to operate efficiently in its designated mode, avoiding the need for continuous high fuel consumption required by nozzle-vectored systems.
Solution Approach 2:
The tilt wings can rotate between horizontal and vertical positions, dynamically changing the configuration of the aerial vehicle. During horizontal flight, the tilt wings are positioned horizontally to maximize wing efficiency and minimize drag. During VTOL, they rotate to vertical position to direct thrust downward, enabling the vehicle to adapt its aerodynamic characteristics to different flight phases and optimize fuel consumption.
2Adaptability or versatility
If helicopter rotors are used for vertical take-off and landing, then VTOL capability is achieved, but forward speed and range are limited due to inefficiency compared to fixed-wing aircraft
Solution Approach 1:
The fixed wings serve multiple functions: they provide primary lift during horizontal flight like conventional fixed-wing aircraft, and they also contribute to vertical lift generation during VTOL operations when combined with the tilt wings. This multi-functionality allows the aerial vehicle to achieve both efficient high-speed horizontal flight and vertical take-off/landing capability, overcoming the speed limitations of traditional helicopters.
3Adaptability or versatility
If helicopter rotors are used, then vertical take-off and landing is achieved, but safety is reduced due to problems such as rotor failures, ground resonance, and loss of control
Solution Approach 1:
The lifting function is segmented between fixed wings and tilt wings with ducted fans, eliminating the use of traditional helicopter rotors. This segmentation removes the associated safety risks of rotor failures, ground resonance, and loss of control. The ducted fan configuration within the tilt wings provides inherent safety advantages by enclosing the rotating blades, preventing foreign object damage, and maintaining control authority even in adverse conditions.
Solution Approach 2:
The ducted fan configuration uses enclosed protective shrouds around the rotating elements, which can be designed as replaceable components. This approach allows for simpler, more robust construction that can withstand harsh conditions and be easily replaced if needed, enhancing overall system reliability and safety compared to complex rotor assemblies.
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 multi-mode aerial vehicle achieves higher aerodynamic performance, stability, and safety by streamlining development, reducing costs, and enhancing controllability, with improved thrust, lift, and horizontal speed, enabling efficient operation in various environments, including confined spaces and water surfaces.
Implementation Method 1
a right tilt wing attached at a first side to a free end of the right fixed wing wherein the right tilt wing is rotatable ninety degrees about its axis
Implementation Method 2
a tilt tail located within the curved guide slot at the rear end of the elongated fuselage, wherein the tilt tail is rotatable ninety degrees within the curved guide slot
Implementation Method 3
an elongated fuselage having a front end, a rear end with a curved guide slot, a right side, a left side, and a wing-in-ground (WIG) effect bottom
Implementation Method 4
dual counter-rotating rotors positioned at an underside of the duct
Data Source
AI summary
A multi-mode aerial vehicle hybrid wing includes a fixed wing configured to extend from a side of an elongated fuselage and double over its longitudinal axis, a tilt wing attached at a first side to a free end of the fixed wing wherein the tilt wing is rotatable ninety degrees about its axis, and a duct attached to a second side of the tilt wing. The duct includes a plurality of pivotal control surfaces positioned at a top entrance of the duct, dual counter-rotating rotors positioned at an underside of the duct, a plurality of cross stators positioned at a back entrance of the duct, and a plurality of stator pivotal control surfaces within each of the cross stators of the duct. The multi-mode aerial vehicle hybrid wing also includes a winglet attached to the duct opposite to the tilt wing.