eVTOL Rotor Pod Vertical Separation for Noise and Stability
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Solution Overview
Problem
Current VTOL aircraft face challenges in achieving efficient vertical flight, stability, and controllability, especially during engine/motor failure, due to limitations in power-to-weight ratios and rotor interference, which affect noise levels, battery consumption, and overall system efficiency.
Innovation Solution
A VTOL aircraft design featuring a fuselage with forward and aft pairs of port and starboard rotor pods, where one-half of the rotor assemblies rotate in one direction and the other half in the opposite direction, with aft wings in a gull wing configuration and pusher propeller assemblies, positioned to maintain equilibrium and stability, even during rotor failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If multiple rotors are used for VTOL capability, then lift and control are improved, but rotor interference increases noise and battery consumption
Solution Approach 1:
The patent positions rotors at different vertical heights (elevations) rather than in the same horizontal plane. The first rotor assembly is at a first height and the second rotor assembly is at a second height, creating vertical separation that reduces rotor interference and noise while maintaining lift generation capability
Solution Approach 2:
The rotor system is divided into multiple independent rotor assemblies positioned at different locations and heights. Each rotor assembly can be independently controlled, allowing for optimized performance and reduced interference between rotors
2Power
If multiple rotors are used for VTOL capability, then lift and control are improved, but battery consumption increases
Solution Approach 1:
By vertically separating the rotor assemblies to different heights, the patent reduces aerodynamic interference between rotors, which improves overall system efficiency and reduces battery consumption while maintaining the required lift generation capability
Solution Approach 2:
The patent changes the spatial parameters of rotor positioning, specifically the vertical elevation of each rotor assembly, to optimize the balance between lift generation and energy consumption by minimizing harmful rotor interactions
3Object-generated harmful factors
If rotor displacement is increased for forward flight, then rotor interference is reduced, but vehicle footprint increases
Solution Approach 1:
Instead of increasing horizontal rotor displacement which would enlarge the vehicle footprint, the patent utilizes the vertical dimension by positioning rotor assemblies at different heights. This approach reduces rotor interference while maintaining a compact horizontal footprint suitable for urban air mobility
4Ease of operation
If distributed propulsion is used, then controllability and stability are improved, but system complexity increases
Solution Approach 1:
The distributed propulsion system is segmented into multiple independent rotor assemblies, each capable of independent control. This segmentation provides enhanced controllability and stability while managing system complexity through modular architecture
Solution Approach 2:
The rotor assemblies serve multiple functions: they provide lift during VTOL operations, contribute to forward thrust during wing-born flight, and enable control moments for stabilization. This multi-functionality reduces the need for separate control mechanisms, managing overall system 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
This design enhances stability and controllability by ensuring zero moments about the Y and X-axes, reducing noise and battery consumption, and improving overall system efficiency while maintaining VTOL capability.
Implementation Method 1
one large main rotor for lift generation
Implementation Method 2
rotor assemblies rotate in one direction and the other half in the opposite direction
Implementation Method 3
a smaller rotor to counteract main rotor torque to achieve stabilization
Implementation Method 4
the sum of moments and forces will continue to add up to zero, so the static equilibrium is obtained
Implementation Method 5
pusher propeller assemblies
Data Source
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AI summary
Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.