VTOL Multi-Rotor Configuration With Partial Wing
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Solution Overview
Problem
Traditional VTOL multi-rotor designs face challenges in scalability and range due to cumbersome rotor speed adjustments and limited suitability for longer sustained flight paths.
Innovation Solution
The implementation of a multi-rotor vehicle configuration that includes two main lifting rotors, auxiliary rotors, and horizontal thrust rotors, combined with a partial wing structure to enhance lift and control, while minimizing interference between rotor and wing performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional multi-rotor VTOL designs use multiple fixed-pitch rotors configured in the horizontal plane to provide lift and thrust, then the aircraft can achieve vertical takeoff and landing capability, but the rotor speed adjustments become cumbersome and the design lacks scalability
Solution Approach 1:
The invention segments the rotor system into distinct functional groups: main lift rotors (providing primary vertical lift), auxiliary lift rotors (providing additional lift and control), and thrust rotors (providing forward thrust). This segmentation allows independent control of each rotor group, simplifying the control architecture and making speed adjustments more manageable compared to traditional designs where all rotors must be controlled uniformly.
Solution Approach 2:
The invention employs variable-pitch rotors instead of fixed-pitch rotors, allowing dynamic adjustment of blade pitch angles in addition to rotational speed control. This dynamic capability enables more precise and efficient control of lift and thrust forces, reducing the complexity of speed adjustments and improving overall vehicle controllability.
2Device complexity
If traditional VTOL designs use quad copter configuration with four rotors for simplified flight control, then the control system becomes easier to manage, but the design creates scalability issues and limited range for sustained flight
Solution Approach 1:
The invention creates a multi-functional rotor system where rotors can serve different purposes: main lift rotors for primary vertical support, auxiliary lift rotors for additional lift and attitude control, and thrust rotors for forward propulsion. This universal design allows the same basic rotor structure to fulfill multiple functions, enabling scalability from vertical flight to sustained horizontal flight without requiring a complete redesign.
Solution Approach 2:
The invention adds a vertical dimension to the rotor arrangement by positioning auxiliary lift rotors above the main lift rotors in a stacked configuration. This three-dimensional arrangement allows for better weight distribution, improved control authority, and enhanced scalability compared to traditional horizontal planar configurations, while maintaining relatively simple control logic.
3Ease of operation
If traditional VTOL aircraft manage forward thrust by varying rotor speeds to change thrust and torque, then the vehicle can achieve directional control, but the design is not suited for longer sustained flight paths due to limited efficiency
Solution Approach 1:
The invention segments the thrust generation function into dedicated thrust rotors with horizontal rotational planes, separate from the vertical lift rotors. This allows independent optimization: lift rotors can operate at efficient speeds for vertical support while thrust rotors provide forward propulsion. This segmentation significantly reduces power consumption during sustained flight compared to traditional designs where all rotors must work together for both lift and thrust.
Solution Approach 2:
The invention changes the operational parameters by introducing variable-pitch capability to the rotors. By adjusting blade pitch angles, the system can optimize the relationship between thrust production and power consumption across different flight conditions, enabling efficient sustained flight paths that traditional fixed-pitch designs cannot achieve.
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 configuration improves flight control efficiency, extends range, and reduces power consumption by decoupling pitch and yaw controls from main lifters, allowing for more efficient use of rotors and wings.
Implementation Method 1
at least two main rotors...configured to generate lift for the vehicle
Implementation Method 2
at least one auxiliary rotor...configured to generate lift for the vehicle
Implementation Method 3
at least two horizontal thrust rotors...configured to generate thrust in a forward direction
Implementation Method 4
at least one partial wing structure...configured to provide additional lift for the vehicle
Data Source
AI summary
A system of a multi-rotor aircraft that capitalizes on the advantages of fixed wing elements combined with rotary wing structures. The fixed wing elements can help to generate lift once the aircraft is airborne and can thus reduce the need for larger lifting rotors which can allow for longer flight times and distances. Additionally, the systems disclosed herein take advantage of a partial in-wing configuration with a number of rotors to reduce the overall footprint of the vehicle while maintaining the flight efficiency that comes with combining features of fixed and rotary wing elements, and increasing operator safety by shrouding rotating parts. The unique configurations allow for a decoupling of the pitch, yaw and roll authority to reduce the complexity in control systems and improve the flight efficiency of the aircraft. Additional configurations implement the use of smaller thrust rotors that can be used to generate thrust as well as control yaw and thus counteract any remaining unbalanced torque.