Annular Ducted Propeller Rotors for Longer-Range Electric Aircraft
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Solution Overview
Problem
Existing drones and aircraft for personal air mobility face challenges with reduced flight range, inefficient propeller rotors, and complex motor systems that do not provide optimal power, torque characteristics, and high energy consumption.
Innovation Solution
The aircraft incorporates high-efficiency annular propeller rotors driven by piezoelectric or axial flow electric motors, with a high torque/weight ratio, and a simple, lightweight, stable structure for enhanced control and vertical thrust, integrated with annular propellers within wing surfaces and additional upper bearing wings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If conventional propeller rotors are used in drones and small aircraft, then the basic flight function is achieved, but the flight range is reduced and energy consumption is high
Solution Approach 1:
The patent applies parameter changes by optimizing propeller blade geometry including airfoil cross-sections, twist angles, and chord distributions to maximize aerodynamic efficiency. The propeller design parameters are specifically tuned to reduce induced losses and improve thrust generation, directly extending flight range while reducing energy consumption in electric aircraft and drones
2Productivity
If conventional propeller rotors are used, then basic propulsion is achieved, but rotor efficiency is poor
Solution Approach 1:
The patent employs parameter changes by optimizing blade element geometry including airfoil selection, twist distribution, and chord length variations along the blade span. These parameter optimizations minimize induced drag and improve the efficiency of converting rotational power to thrust, reducing energy losses in the propeller system
Solution Approach 2:
The patent applies dynamics through variable pitch propeller mechanisms that allow real-time adjustment of blade angles during flight. This dynamic adaptation enables the propeller to maintain optimal efficiency across varying flight conditions, speeds, and power settings, maximizing productivity while minimizing energy losses
3Power
If high power motors are used to achieve necessary torque characteristics, then power requirements are met, but the torque/weight ratio is compromised and energy consumption increases
Solution Approach 1:
The patent applies parameter changes by optimizing motor design parameters including magnetic material selection, winding configurations, and stator-rotor geometry to achieve high power density. These parameter optimizations enable motors to deliver necessary torque characteristics while minimizing weight, improving the torque/weight ratio for electric aircraft applications
4Power
If complex motor systems are used to achieve necessary torque characteristics, then power requirements are met, but the system construction becomes complicated
Solution Approach 1:
The patent applies the extraction principle by removing unnecessary intermediate components and simplifying the motor architecture. Direct-drive motor configurations eliminate the need for complex gear trains, belts, or reduction mechanisms, achieving necessary torque characteristics through direct electromagnetic coupling while significantly reducing system construction complexity
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 solution achieves extended flight range, high-speed rotation, minimal energy consumption, and improved stability and control, making it suitable for drones and personal air mobility applications.
Implementation Method 1
driven by piezoelectric or axial flow electric motors
Implementation Method 2
driven by piezoelectric or axial flow electric motors
Implementation Method 3
high efficiency propeller rotors... capable of high vertical thrust
Data Source
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AI summary
An aircraft, in particular a drone or an aircraft for personal air mobility, comprises at least one horizontal planar structure (2), wherein four ducted propeller rotors (3) with vertical axis are incorporated, which are substantially coplanar with each other. Each of the four propeller rotors (3) comprises a rotating ring (4) rotatably mounted within a circular opening with a vertical axis (5), formed through said at least one horizontal planar structure (2). The rotating ring (4) is configured in such a way as to define an annular wall for the ducting of the air flow produced by the propeller rotor (3). Each of the four propeller rotors (3) comprises one or more blades (7) which extend radially from the body of the rotating ring (4) towards the central axis of the propeller rotor (3), and which have their tips terminating at a distance from the central axis of the propeller rotor (3), in such a way that each propeller rotor is in the form of an annular propeller. The rotating ring (4) of each propeller rotor (3) is controlled in rotation by an electric actuator consisting of an axial flow annular electric motor (10) or by a piezoelectric annular motor, comprising a system of piezoelectric actuators.