VTOL UAV Foldable Wing Twin-Ducted Fan Power System
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Solution Overview
Problem
Existing vertical take-off and landing aerial vehicles face challenges such as unstable airflow, complex and vulnerable tilting mechanisms, low power efficiency, and difficulty in achieving high-speed cruising due to large aerodynamic resistance from exposed rotors and tilting systems, which affect stability and performance, especially in adverse weather conditions.
Innovation Solution
A vertical take-off and landing unmanned aerial vehicle with a foldable fixed wing and a twin-ducted fan power system, where the ducted fans are symmetrically arranged on the rear fuselage, generating lift and thrust while reducing aerodynamic noise and increasing lift-to-weight ratio, and the foldable wing configuration minimizes frontal area during take-off and landing, enhancing stability and anti-wind capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a tilt rotor mechanism is used to achieve vertical take-off and landing, then both helicopter rotor and fixed-wing propeller functions are achieved, but the structure becomes complicated and vulnerable to damage
Solution Approach 1:
The aircraft is divided into two independent power systems: a main rotor system for vertical flight and a pusher propeller system for horizontal flight. This segmentation eliminates the need for a complex tilting mechanism while achieving dual flight mode capability. Each system operates independently without mechanical coupling, reducing overall system complexity and vulnerability.
2Adaptability or versatility
If an auxiliary vertical lift system with exposed rotor is added to traditional fixed-wing aircraft, then vertical take-off and landing capability is achieved, but aerodynamic resistance increases during horizontal flight
Solution Approach 1:
The main rotor is completely extracted from the horizontal flight configuration. During cruise, only the pusher propeller operates, eliminating the aerodynamic drag of an exposed rotor. The rotor blades are stowed in a streamlined fairing that contours with the fuselage, removing the harmful aerodynamic effect while preserving vertical flight capability when the rotor is deployed.
3Use of energy by moving object
If a tail-sitter configuration is used for vertical take-off and landing, then power system efficiency is improved, but flight state transition becomes difficult to control and affected by wind
Solution Approach 1:
The aircraft employs a dynamic transition process where the main rotor pitch angle is gradually reduced while the pusher propeller thrust is increased. This continuous adjustment of power distribution enables smooth, controlled transitions between vertical and horizontal flight modes, making the process stable and less sensitive to wind conditions compared to rigid tail-sitter configurations.
4Force
If a large disc radius rotor is used to achieve thrust-to-weight ratio of 1 or more, then vertical lift capability is achieved, but aerodynamic resistance increases during horizontal flight
Solution Approach 1:
The lifting function is segmented between two systems: the large-diameter main rotor provides vertical lift during hover and take-off, while the pusher propeller provides forward thrust during horizontal flight. This functional segmentation allows the rotor to be optimized for vertical lift without compromising horizontal flight performance, as the rotor is stowed during cruise to eliminate its aerodynamic drag.
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 twin-ducted fan power system improves efficiency and reduces energy consumption during take-off, landing, and flight, increasing lift coefficient and stability, allowing for longer flight times and high-speed cruising with enhanced anti-disturbance capabilities in crosswind environments.
Implementation Method 1
the ducted fans are symmetrically arranged on the rear fuselage, generating lift and thrust
Implementation Method 2
the ducted fans are symmetrically arranged on the rear fuselage, generating lift and thrust
Implementation Method 3
the foldable wing configuration minimizes frontal area during take-off and landing, enhancing stability and anti-wind capabilities
Implementation Method 4
the ducted fans are symmetrically arranged on the rear fuselage, generating lift and thrust while reducing aerodynamic noise
Data Source
AI summary
A vertical take-off and landing (VTOL) unmanned aerial vehicle having a foldable fixed wing and a twin-ducted fan power system (7) arranged at a tail portion of a fuselage in a transverse and tail propulsion arrangement provides lift for vertical take-off and landing and propulsion for horizontal flight. By means of deflection of a control servo plane arranged at a duct exit, a vectored thrust is provided to enable a fast attitude change. When the aerial vehicle takes off and lands vertically/flies at a low speed, the wing is folded to reduce the frontal area exposure to crosswind. When the aerial vehicle is flying horizontally, the wing is expanded to obtain larger lift. A Coanda effect is created at a trailing edge of the wing by suction of the duct to improve performance.