eVTOL Rotor Architecture With Blade Pitch Control for Fewer Rotors
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Solution Overview
Problem
Existing eVTOL aircraft designs face challenges in efficiently carrying a payload of at least 500 pounds while using a reduced number of rotors, balancing vertical lift and forward propulsion, and ensuring safety and efficiency, particularly in transitioning between vertical and forward flight modes.
Innovation Solution
An electric vertical takeoff and landing aircraft is engineered with a reduced number (2-4) of variable speed rigid rotors, utilizing individual blade control actuators for pitch control and a large wing for efficient lift and thrust, with integrated rotor drive systems and a slotted flap for roll control, enabling safe and efficient operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a reduced number of rotors (2-4) is used in eVTOL aircraft, then device complexity is reduced and ease of operation is improved, but reliability deteriorates because failure of a single rotor can crash the aircraft
Solution Approach 1:
Each rotor in the 2-4 rotor configuration is designed to perform multiple functions: providing vertical lift during hover, generating forward thrust during cruise, and contributing to both lift and drag control during transition phases. This multi-functionality allows the reduced number of rotors to compensate for the loss of redundancy, as each rotor becomes more critical and versatile, thereby maintaining system reliability despite fewer components
Solution Approach 2:
The rotors are designed with variable pitch capability and tilting mechanisms that allow dynamic adjustment of blade angle and rotor orientation. This dynamic adaptability enables each rotor to optimize its performance across different flight phases (hover, transition, cruise), ensuring that the reduced number of rotors can reliably handle all operational requirements without compromising safety
2Power
If rotors are designed for high power output to carry 500+ pounds payload, then power loading is improved, but noise levels increase and efficiency in forward flight deteriorates
Solution Approach 1:
Variable pitch control allows the rotor blades to dynamically adjust their angle of attack based on flight phase. During hover, blades are positioned for maximum lift; during forward flight, pitch is reduced to optimize thrust efficiency. This dynamic adjustment enables high power output when needed while reducing noise and improving efficiency during cruise, as the rotors operate at optimal angles for each flight regime
Solution Approach 2:
The system changes operational parameters including rotor speed, blade pitch angle, and rotor tilt angle to optimize performance across different flight phases. By varying these parameters, the aircraft achieves high power loading capability for payload transport while maintaining lower noise levels and improved efficiency during forward flight, as each parameter is optimized for its specific operational context
3Device complexity
If rotors are positioned fixed with respect to wings, then device complexity is reduced, but adaptability deteriorates because rotors cannot tilt from vertical lift to forward propulsion positions
Solution Approach 1:
Each rotor assembly is designed as a multi-functional unit that can perform vertical lift, forward propulsion, and transition functions. The rotors are mounted on tilting mechanisms that allow them to change orientation between vertical (for hover) and horizontal (for forward flight) positions. This universal design enables the same rotor structure to adapt to different flight modes without requiring separate propulsion systems for each phase
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 achieves safe and efficient vertical takeoff and forward flight, with low noise, high power loading, and reduced risk of accidents, allowing for commercial use with a payload of at least 500 pounds.
Implementation Method 1
a large wing for efficient lift and thrust
Implementation Method 2
utilizing individual blade control actuators for pitch control and a large wing for efficient lift and thrust
Implementation Method 3
Battery and engine architecture for VTOL aircraft
Data Source
AI summary
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.