VTOL Aircraft Rotor Dynamics for High-Speed Flight

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

There is a long-felt need for a vertical take-off and landing aircraft that can achieve high-speed flight while minimizing downwash during hover, and operating entirely on battery power to address climate change and flexibility in power generation.

Innovation Solution

The aircraft design incorporates a lifting structure, dual rotors with independently controlled blade attack angles, an auxiliary propulsion unit for forward thrust, and a control system that allows for three-axis control during high-speed flight modes.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If the aircraft uses rotors for vertical take-off and landing, then vertical flight capability is achieved, but high-speed flight capability deteriorates

Engineering Contradiction:

Improvevertical flight capabilityVSAvoidhigh-speed flight capability

Core Design Contradiction:

Adaptability or versatilityVSSpeed

Solution Approach 1:

The aircraft employs dynamic reconfiguration of rotor functions. During vertical flight, rotors rotate freely to generate lift. During high-speed flight, the rotors are locked into fixed azimuth positions and function as static wings, while a propeller provides forward thrust. This dynamic transformation allows the same rotor structure to serve dual purposes across different flight regimes.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The rotor system is designed to perform multiple functions: generating lift during vertical take-off and landing, and acting as aerodynamic wings during high-speed forward flight. The auxiliary propulsion unit also serves dual purposes by providing forward thrust in both flight modes. This multi-functionality resolves the contradiction between vertical and high-speed flight capabilities.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Force

If the aircraft uses large rotors for vertical take-off and landing, then lift capability is improved, but downwash increases

Engineering Contradiction:

Improvelift capabilityVSAvoiddownwash

Core Design Contradiction:

ForceVSObject-generated harmful factors

Solution Approach 1:

The rotor blade attack angles are dynamically adjusted based on flight conditions. During hover, the attack angles are optimized to minimize downwash while maintaining sufficient lift. During high-speed flight, the rotors are locked at fixed azimuth angles and function as static wings, eliminating rotor-induced downwash entirely.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The control system varies the attack angle of rotor blades as a key parameter to optimize performance. By adjusting attack angles, the system can achieve the same lift with reduced downwash during hover, and transition to wing-mode during high-speed flight where downwash is eliminated.

Inventive Principle:

Principle #35Parameter changes

3Adaptability or versatility

If the aircraft uses conventional propulsion systems, then power generation flexibility is achieved, but environmental sustainability deteriorates

Engineering Contradiction:

Improvepower generation flexibilityVSAvoidenvironmental sustainability

Core Design Contradiction:

Adaptability or versatilityVSObject-generated harmful factors

Solution Approach 1:

The patent replaces conventional mechanical propulsion systems (combustion engines, turbines) with an electric propulsion system driven by battery power. This substitution eliminates direct emissions while maintaining the flexibility to use various battery technologies and power management systems, thus resolving the contradiction between flexibility and environmental sustainability.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

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 enables the aircraft to transition seamlessly from vertical take-off and landing to high-speed flight, reducing downwash and achieving efficient battery-powered operation, thus addressing the challenges of high-speed capability, low downwash, and environmental sustainability.

Implementation Method 1

a first rotor 102 comprising: i) a first blade 121; and ii) a second blade 122... adapted to be rotated about a first mast 103 to provide lift during a first flight mode

Methodology Applied

Scientific EffectLift (aerodynamic): Aerofoil

Implementation Method 2

an auxiliary propulsion unit 110... adapted to provide forward thrust during said second flight mode

Methodology Applied

Scientific EffectThrust (aerodynamic): Jet

Implementation Method 3

a control system 111 adapted to independently control an attack angle of each of said blades... adapted to provide one or more of pitch, yaw, or roll control to said aircraft

Methodology Applied

Scientific EffectAngle of attack control: Aerofoil

Data Source

PatentUS12330778B2High-speed, vertical take-off and landing aircraft

Publication Date: 2025.06.17 KYMATICS LLC

AI summary

A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.