Variable Pitch Rotor Assembly for VTOL Aircraft Thrust Vectoring
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Solution Overview
Problem
Existing multi-rotor aircraft systems with fixed pitch rotors are ill-suited for efficient operation in both vertical take-off and landing (VTOL) and fixed wing flight, as they lack the necessary thrust control and thermal management for increased maneuverability and endurance.
Innovation Solution
A rotor assembly with variable pitch control applied to a brushless direct current motor, enabling instantaneously controlled rotor airfoil pitch and enhanced thermal management, allowing for efficient thrust vectoring and heat rejection, which is integrated into an articulated propulsion system for aircraft transitioning between VTOL and fixed wing modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If fixed pitch rotors are used in multi-rotor aircraft systems, then the structure is simpler and weight is reduced, but the aircraft lacks efficient operation capability in both VTOL and fixed wing flight modes
Solution Approach 1:
The patent applies variable pitch control to the rotor blades, allowing the pitch angle to be dynamically adjusted during operation. This enables the same rotor assembly to efficiently operate in both VTOL and fixed wing flight modes by changing the blade pitch angle according to the flight phase, thereby resolving the contradiction between adaptability and structural simplicity.
Solution Approach 2:
The patent changes the operational parameters of the rotor system by introducing variable pitch capability. By adjusting the pitch angle parameter, the rotor can be optimized for different flight conditions (vertical flight vs. horizontal flight), achieving multi-mode operation without fundamentally changing the rotor structure.
2Ease of operation
If variable pitch control is implemented in rotor assemblies, then thrust control and maneuverability are improved, but the device complexity and weight increase
Solution Approach 1:
The patent replaces complex mechanical variable pitch mechanisms with a more streamlined control system applied to the rotor assembly. The variable pitch control is integrated into the existing motor and rotor structure, using electrical control signals to adjust blade pitch, thereby reducing mechanical complexity while maintaining thrust control capability.
Solution Approach 2:
The rotor assembly is designed to perform multiple functions: it provides both lift and thrust vectoring capabilities through integrated variable pitch control. This multi-functionality is achieved within a unified rotor structure that combines motor, rotor blades, and pitch control mechanisms, avoiding the need for separate systems and reducing overall complexity.
3Use of energy by moving object
If variable pitch control is applied to brushless direct current motors, then propulsion efficiency is optimized for different flight modes, but the device complexity increases
Solution Approach 1:
The patent merges the variable pitch control mechanism with the brushless direct current motor assembly into an integrated propulsion unit. The pitch control system is combined with the motor housing and rotor structure, allowing efficient energy transfer from the motor to the rotor blades while maintaining a compact, unified design that minimizes complexity.
Solution Approach 2:
The integrated motor-rotor-pitch control assembly is designed to automatically adjust its operational parameters based on flight conditions. The system self-regulates the pitch angle and motor power output to optimize propulsion efficiency for the current flight mode, reducing the need for external control complexity.
4Reliability
If thermal management is enhanced in the rotor assembly, then reliability and endurance are improved, but the device weight and complexity increase
Solution Approach 1:
The rotor assembly utilizes the airflow generated during rotation to provide passive cooling for the brushless direct current motor. The rotating blades create a natural airflow that dissipates heat from the motor, eliminating the need for separate active cooling systems and reducing overall weight while maintaining reliability.
Solution Approach 2:
The system recovers the thermal energy that would otherwise be wasted by using it for beneficial purposes. The heat generated by the motor during operation is managed through the rotor assembly structure, which facilitates heat dissipation into the surrounding air, thereby improving reliability without requiring additional heavy cooling components.
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 solution provides increased aircraft maneuverability, controllability, and endurance by optimizing propulsion efficiency, reducing weight, and enhancing thermal management, while maintaining a constant rotor tip speed for reduced acoustic detection and improved reliability.
Implementation Method 1
brushless direct current motor
Implementation Method 2
enhanced thermal management
Implementation Method 3
heat rejection
Data Source
AI summary
An aircraft employs articulated, variable-position electric rotors having different operating configurations and transitions therebetween, as well as variable-pitch airfoils or blades, for generating vectored thrust in the different configurations. Control circuitry generates rotor position signals and blade pitch signals to independently control rotor thrust, rotor orientation and rotor blade pitch of the variable-position rotors in a manner providing (i) the transitions among the operating configurations for corresponding flight modes of the aircraft, which may include both vertical takeoff and landing (VTOL) mode as well as a forward-flight mode, and (ii) commanded thrust-vectoring maneuvering of the aircraft in the different configurations, including tailoring blade pitch to optimize aspects of aircraft performance.