Helicopter Vibration Control via Circular Force Generators
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Solution Overview
Problem
Existing vibration control systems for aircraft with rotating components, such as helicopter rotors, face challenges in effectively minimizing vibrations between the nonrotating body and rotating hub, leading to discomfort and structural stress.
Innovation Solution
A vibration control system that includes a rotary wing aircraft with a nonrotating aerostructure body and a rotating hub, equipped with sensors and circular force generators connected through a data communications network, allowing for the generation of controlled rotating forces to counteract vibrations sensed by sensors on the nonrotating body.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a vibration control system is implemented with sensors and force generators, then vibration reduction is achieved, but device complexity increases
Solution Approach 1:
The vibration control system is divided into separate functional modules: vibration sensors mounted on the nonrotating body, circular force generators, and a control system. Each component performs a specific function, allowing the system to be implemented incrementally and maintained independently.
Solution Approach 2:
A distributed data communications network serves as an intermediary, linking the vibration sensors, control system, and circular force generators. This modular communication architecture reduces overall system complexity by standardizing interfaces between components.
2Object-affected harmful factors
If circular force generators are used to counteract vibrations, then vibration reduction is achieved, but weight of the system increases
Solution Approach 1:
The system dynamically adjusts the magnitude and phase parameters of the rotating forces generated by the circular force generators based on real-time vibration measurements. This allows optimal vibration cancellation with minimal force generation, reducing the required generator size and weight.
Solution Approach 2:
The circular force generators are designed to serve multiple functions: vibration cancellation, balance control, and potentially propulsion assistance. This multi-functionality justifies the weight addition by providing multiple benefits from a single system component.
3Measurement precision
If real-time vibration sensing and force generation are implemented, then vibration control precision is improved, but use of energy increases
Solution Approach 1:
The system operates in periodic cycles: sensors detect vibration, the control system processes the data, and force generators apply counteracting forces at regular intervals synchronized with the rotation frequency. This periodic operation allows the system to maintain precision while managing energy consumption through duty-cycled operation.
Solution Approach 2:
The control system continuously receives feedback from vibration sensors and adjusts the force generator output in real-time. This closed-loop feedback mechanism ensures precise vibration control while optimizing energy usage by applying force only when and where needed, rather than continuous operation.
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
The system effectively reduces vibrations by generating controllable rotating forces that match the frequency and phase of the rotating hub, thereby minimizing disturbances sensed by the nonrotating body, enhancing comfort and structural integrity.
Implementation Method 1
a circular force generator for producing a rotating force having a controllable rotating force magnitude and a controllable rotating force phase
Data Source
AI summary
A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.