Fixed-Wing VTOL Rotor Layout for Lift and Control Balance
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Solution Overview
Problem
Fixed-wing VTOL aerial vehicles face challenges in optimizing rotor distribution for improved lift capability, weight management, and simplified control, especially when transitioning between vertical take-off and cruise flight modes.
Innovation Solution
The design incorporates modular propeller-rotor systems with X-shaped, H-shaped, and K-shaped configurations, allowing for detachable or rotatable fixed wings, optimized empennage, and angular frames to enhance lift, stability, and control, enabling operation as both fixed-wing and multi-copter aerial vehicles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If the number of rotors is increased to improve lift capability, then the lift capability is improved, but the weight increases due to additional rotors and support structure
Solution Approach 1:
The patent combines multiple rotor systems into an integrated configuration where rotors are positioned at the corners of a rectangular platform. This merging approach allows the rotors to work together as a unified lift system, providing enhanced lift capability while sharing common support structures and control mechanisms, thereby reducing the cumulative weight penalty of individual rotor systems.
Solution Approach 2:
The rotor system is designed to serve multiple functions: providing vertical lift during takeoff and landing, enabling hover capability, and contributing to vehicle stabilization. This multi-functionality reduces the need for separate dedicated components, thereby minimizing additional weight while maximizing lift capability across different flight phases.
2Force
If the number of rotors is increased to improve performance, then the lift capability is improved, but the device complexity increases due to more complex control algorithms
Solution Approach 1:
The patent employs an asymmetric control architecture where one rotor is designated as independent while the other three rotors operate in a coordinated group. This asymmetric division simplifies the control algorithm by reducing the computational burden from managing all rotors independently to managing one independent rotor and one coordinated group, thereby maintaining enhanced lift capability with reduced control complexity.
Solution Approach 2:
The control system is segmented into two functional modules: an independent single-rotor controller and a multi-rotor coordinated controller. This segmentation allows each module to handle simpler control tasks independently, reducing the overall complexity of the control algorithm while maintaining the enhanced lift capability provided by the four-rotor configuration.
3Ease of operation
If conventional multi-copter rotor distribution is used with point symmetrical configuration, then the control operation is simplified, but the fixed-wing VTOL configuration cannot achieve optimal lift distribution
Solution Approach 1:
The patent adopts an asymmetric rotor configuration where one rotor is positioned independently and the other three form a triangular group, rather than using symmetric point distribution. This asymmetric arrangement optimizes lift distribution for fixed-wing VTOL operation by placing rotors at strategic locations that align with the aircraft's center of gravity and aerodynamic center, improving both lift efficiency and control characteristics.
Solution Approach 2:
Different regions of the vehicle are assigned different rotor functions: one rotor provides independent thrust control for fine positioning and attitude adjustment, while the other three rotors provide primary lift and coarse positioning. This local differentiation of rotor roles optimizes the overall lift distribution and control characteristics for fixed-wing VTOL operation.
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 provides improved lift capacity, simplified rotor installation and operation, and enhanced stability, allowing the vehicle to function efficiently in both VTOL and cruise modes with reduced weight and complexity.
Implementation Method 1
Each set of propeller-rotors includes four propeller-rotors configured at ends of a set of X-shaped rotor arms for providing vertical lift of the aerial vehicle
Data Source
Figure 1A
Figure 1B
Figure 1C
AI summary
An aerial vehicle (100) includes a fuselage (102) having an angular frame (102A); a fixed wing (104) fixed on an upper side of the fuselage (102); at least two sets of first propeller-rotors and second propeller-rotors each comprising four propeller-rotors (206A,208A) configured at ends of a set of first rotor arms (106B-1 to 106B-3) and a set of second rotor arms (108B-1 to 108B-3) positioned on an underside of the aerial vehicle (100) for vertical lift of the aerial vehicle (100). The first rotor arms (106B-1 to 106B-3) and the second rotor arms (108B-1 to 108B-3) are any or a combination of X-shaped, H-shaped and K-shaped. The aerial vehicle (100) includes a predefined empennage (110) configured to the fuselage (102) for enabling flight of the VTOL aerial vehicle (100) after the vertical lift of the aerial vehicle (100).