Annular Electric Motor Vibration Suppressor for Rotary-Wing Aircraft
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Solution Overview
Problem
Existing vibration suppressor systems for rotary-wing aircraft are heavy, costly, and unable to adjust in-flight to varying in-plane load frequencies, limiting their effectiveness and increasing maintenance costs.
Innovation Solution
An annular electric motor system with a control system that independently rotates masses about the axis of rotation to reduce in-plane vibrations, allowing for dynamic adjustment of rotational speed and angular position to counteract vibratory loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If spiral spring vibration isolators are used to suppress in-plane vibrations, then vibration suppression is achieved, but the device weight increases significantly
Solution Approach 1:
The patent replaces the mechanical spiral spring system with an active control system using actuators and sensors. The active control system uses electronic signals and feedback control to generate counter-vibrations, eliminating the need for heavy mechanical springs while achieving the same vibration suppression effect.
Solution Approach 2:
The invention transitions from a passive static spring system to a dynamic active control system that can adjust its characteristics in real-time. The active control system modifies its response based on actual vibration conditions, allowing weight reduction while maintaining or improving vibration suppression performance across varying operating conditions.
2Object-affected harmful factors
If spiral spring vibration isolators are designed with precise tolerances for exact spring rates, then vibration suppression effectiveness is improved, but manufacturing costs increase
Solution Approach 1:
The active control system replaces precision-machined mechanical springs with electronically controlled actuators. The control system achieves precise vibration cancellation through software algorithms and feedback control rather than requiring precisely manufactured mechanical components, significantly reducing manufacturing tolerances and costs.
Solution Approach 2:
The invention changes the approach from fixed mechanical parameters (spring rates) to adjustable electronic parameters (actuator forces, control gains). This allows the system to adapt to varying operating conditions through software rather than requiring multiple precision-manufactured components for different conditions.
3Object-affected harmful factors
If passive vibration isolators tuned to predetermined frequency are used, then vibration suppression is achieved at specific frequencies, but the device cannot adjust to varying frequencies in different flight regimes
Solution Approach 1:
The active control system transitions from fixed frequency tuning to dynamic frequency adaptation. Sensors detect actual vibration frequencies and the control system continuously adjusts actuator commands to maintain effective suppression across varying frequencies encountered in different flight regimes.
Solution Approach 2:
The invention implements a closed-loop feedback control system where sensors monitor vibration levels and frequencies, and the control system uses this information to adjust actuator commands in real-time. This feedback mechanism enables automatic adaptation to changing vibration characteristics without manual retuning.
4Object-affected harmful factors
If heavy vibration isolators are installed on the rotor system, then vibration suppression is achieved, but the useful payload capacity of the helicopter is reduced
Solution Approach 1:
The active control system replaces heavy passive mechanical isolators with lightweight electronic control components including sensors, actuators, and a control computer. This substitution dramatically reduces the weight of the vibration suppression system while maintaining or improving its effectiveness.
Solution Approach 2:
The transition to a dynamic active control system enables the use of much lighter components compared to static mechanical isolators. The system achieves vibration suppression through controlled forces from lightweight actuators rather than relying on the mass and stiffness of heavy mechanical springs.
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 reduces the weight and cost of vibration suppression while enabling in-flight adjustment to varying frequencies, enhancing the aircraft's lifting capacity and reducing maintenance costs by effectively mitigating vibrations across different flight regimes.
Implementation Method 1
An annular electric motor system defined about an axis of rotation of a rotating system
Implementation Method 2
independently rotating a multiple of independently rotatable masses disposed about an axis of rotation to reduce in-plane vibration
Data Source
AI summary
A vibration suppressor system includes an annular electric motor system which independently controls rotation of at least two masses about the axis of rotation to reduce in-plane vibration of the rotating system. A method of reducing vibrations in a rotary-wing aircraft includes independently controlling a relative angular position of a multiple of independently rotatable masses to reduce vibrations of a main rotor system.