Induction Magnet Yaw Control for Rotor Systems
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Solution Overview
Problem
Rotary wing aircraft face challenges in yaw control during autorotation, as the up-flow of air reduces the ability to generate torque and control, leading to increased complexity, weight, and cost with additional yaw control mechanisms like thrusters and large rudders.
Innovation Solution
A rotor system with a power generation system that includes a generator stator and rotor coupled with induction type magnets, where a control unit selectively delivers power to the magnets to alter torque without decreasing rotational speed, providing yaw control through the power generation system during autorotation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If additional means of yaw control (thrusters and large rudder) are provided, then yaw control capability during autorotation is improved, but device complexity, weight, and cost increase
Solution Approach 1:
The generator is designed to perform multiple functions: during normal operation it generates electrical power, and during autorotation it serves as a torque control device for yaw control. By applying electrical power to the generator during autorotation, the rotor blades experience modified aerodynamic forces that create differential drag, enabling yaw control without additional hardware.
Solution Approach 2:
The existing generator components (stator and rotor) are utilized for yaw control during autorotation. The system uses its own built-in generator to provide the necessary torque control, eliminating the need for external thrusters or large rudders. The generator essentially serves itself by using its electromagnetic components to create the required aerodynamic effects on the rotor blades.
2Ease of operation
If differential collective is used to provide yawing moment, then yaw control is achieved during normal powered flight, but control ability is degraded during autorotation when rotor is in autorotative state
Solution Approach 1:
The system dynamically adapts its control mechanism based on the operational mode. During normal powered flight, differential collective control is used. During autorotation, the control system switches to applying electrical power to the generator, which dynamically modifies the aerodynamic forces on the rotor blades to provide yaw control. This dynamic switching maintains ease of operation across different flight regimes.
Solution Approach 2:
The system changes the control parameter from mechanical collective pitch adjustment to electrical power application to the generator. This parameter change allows the system to maintain yaw control capability across different operational modes. By controlling the electrical power supplied to the generator, the system can precisely control the torque and resulting yaw moment during autorotation.
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 enables effective yaw control during autorotation without reducing rotational speed, reducing the need for additional complex mechanisms, thereby simplifying the aircraft design and reducing weight and cost.
Implementation Method 1
At least one induction type magnet is mounted to at least one of the generator stator and the generator rotor. A control unit is operably coupled to the at least one induction type magnet to selectively deliver power to the at least one induction type magnet to alter a torque of the rotor hub
Data Source
AI summary
A rotor system of an aircraft includes a rotor hub rotatable about an axis of rotation, and a power generation system. The power generation system includes a generator stator and a generator rotor. The generator rotor is coupled to the rotor hub. At least one induction type magnet is mounted to at least one of the generator stator and the generator rotor. A control unit is operably coupled to the at least one induction type magnet to selectively deliver power to the at least one induction type magnet to alter a torque of the rotor hub without decreasing a rotational speed of the rotor hub.