Triangulated Ducted Fan V/STOL Layout for High-Speed Cruise
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Solution Overview
Problem
Existing VTOL and STOL aircraft designs face challenges in achieving high speed, range, comfort, and efficiency due to complex control systems, large rotors, limited aerodynamics, and high fuel consumption, making them unsuitable for widespread commercial use.
Innovation Solution
A V/STOL aircraft design featuring a fuselage with ducted fans positioned triangulatively about the center of gravity, allowing for independent control of thrust and lift, and a power transmission system with redundant engines for enhanced safety and performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If helicopters use large-diameter rotors for vertical takeoff and landing, then VTOL capability is achieved, but speed and range are limited
Solution Approach 1:
The patent applies dynamics by making the rotor assembly tiltable between vertical and horizontal positions. When vertical, the rotors provide lift for VTOL operations; when tilted forward, they generate thrust for high-speed forward flight. This dynamic reconfiguration allows the same rotor system to excel at both VTOL and high-speed cruise, resolving the contradiction between adaptability and speed.
2Force
If tiltrotor aircraft use large engine/rotor assemblies for VTOL, then vertical lift is achieved, but aerodynamics of wings are diminished
Solution Approach 1:
The patent segments the propulsion system into dedicated lift rotors mounted on the wings and a separate pusher propeller at the rear. The lift rotors provide vertical lift during VTOL operations without interfering with wing aerodynamics, while the pusher propeller provides efficient thrust during forward flight. This segmentation resolves the contradiction by assigning different functions to different components.
3Speed
If compound helicopters add propellers to increase speed, then forward speed is improved, but complexity of control systems increases
Solution Approach 1:
The patent merges the functions of lift and thrust into a single tilting rotor assembly. By tilting the entire rotor assembly rather than coordinating multiple independent systems, the control mechanism is simplified. The same blades and motor provide both vertical lift and forward thrust, reducing control system complexity while maintaining high speed capability.
4Speed
If fixed-wing aircraft use runways for takeoff and landing, then speed and range are improved, but footprint and infrastructure requirements increase
Solution Approach 1:
The patent creates a multi-functional aircraft that can operate from both traditional runways and small vertical platforms. The tilting rotor system allows the aircraft to perform conventional runway takeoffs and landings when needed, while also enabling vertical operations from small pads. This universality resolves the contradiction by allowing the aircraft to achieve high speed performance without requiring large airport infrastructure.
5Reliability
If helicopters operate at low speeds for safety, then control is simplified, but fuel consumption increases
Solution Approach 1:
The patent uses dynamics to transition from vertical rotor configuration for safe VTOL operations to horizontal propeller configuration for efficient forward flight. The ability to tilt the rotor assembly allows the aircraft to operate safely at low speeds during vertical maneuvers, then efficiently cruise at high speeds where fuel consumption per distance is lower, resolving the contradiction between safety and fuel efficiency.
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 design enables vertical takeoff and landing with high speed and range, reducing fuel consumption and operational complexity, making it suitable for commercial applications on small parcels of land without the need for runways.
Implementation Method 1
A first ducted lift/thrust fan is cantilevered from a forward side portion of the fuselage... A second ducted lift/thrust fan is cantilevered from a forward opposite side portion of the fuselage... A downwardly exhausting ducted lift fan is disposed within the fuselage
Implementation Method 2
A pair of wings extend laterally outward from the fuselage... The pair of ducted lift/thrust fans are selectively, rotatably movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust
Implementation Method 3
A power transmission system with redundant engines for enhanced safety and performance
Implementation Method 4
The pair of ducted lift/thrust fans are selectively, rotatably movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust
Data Source
AI summary
A vertical/short takeoff and landing aircraft includes a pair of ducted lift/thrust fans that are rotatably movable between a first vertical lift position and a second horizontal thrust position. The lift/thrust fans cantilever from a fuselage of the aircraft, forward of the aircraft's wings. A downwardly exhausting, ducted lift fan is disposed within the aircraft's fuselage, aft of the aircraft's pitch axis. A power plant, disposed within the fuselage, is coupled with the lift/thrust fans and the lift fan by a transmission system. The lift/thrust fans and lift fan are positioned with respect to one another to be triangulated about the aircraft's center of gravity and the aircraft's center of lift.