Helicopter Rotor Blade Control System for Vibration Reduction
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Solution Overview
Problem
Existing helicopter rotor control systems generate excessive noise, vibration, and control loads due to the dynamic motion of rotor blades, which are not effectively addressed by prior methods that focus on dissipating vibrations in materials or structures, leading to increased wear and fuel consumption.
Innovation Solution
A method and apparatus for individual blade control, where each rotor blade is dynamically controlled using blade dynamics signals to generate a compensation output for dynamic forces, reducing control loads and noise through a system that includes blade dynamics sensors, actuators, and a control loop that adjusts pitch control signals based on flight control inputs and harmonic analysis.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If a single control signal is phase-shifted to actuate pitch of individual blades, then the rotor control system can maintain simple structure, but it cannot effectively reduce vibration and noise generated by dynamic motion of rotor blades
Solution Approach 1:
The patent divides the rotor control system into independent control channels for each blade. Each blade receives its own control signal that is specifically tailored to compensate for the dynamic forces acting on that individual blade, rather than using a single phase-shifted signal for all blades. This segmentation enables targeted vibration and noise reduction while managing system complexity through modular control architecture.
Solution Approach 2:
The system dynamically adjusts control parameters including signal amplitude, phase, and frequency for each individual blade based on real-time blade dynamics. By changing these parameters individually for each blade rather than using a uniform phase-shifted approach, the system can effectively reduce vibration and noise while maintaining manageable complexity through adaptive control algorithms.
2Object-generated harmful factors
If vibration is dissipated through material or structural modifications, then noise and vibration can be reduced, but durability and wear resistance of rotor and drive train components deteriorate
Solution Approach 1:
The patent replaces passive mechanical vibration dissipation methods (such as vibration dampers and flexible materials) with an active control system that uses sensors and actuators to dynamically counteract vibration forces. This substitution eliminates the need to compromise material durability for vibration reduction, as the active control system addresses vibration through force compensation rather than mechanical dissipation.
3Use of energy by moving object
If individual blade control is implemented to reduce dynamic forces, then control loads and power consumption decrease, but the control system complexity increases
Solution Approach 1:
The system employs feedback mechanisms where sensors detect blade dynamics and control loads, and this information is used to adjust control signals for each blade in real-time. The feedback loop enables the system to optimize power consumption by applying control forces only when and where needed, while managing complexity through established feedback control methodologies.
Solution Approach 2:
The control system dynamically adapts its parameters including signal amplitude, phase, and frequency based on real-time blade conditions and operational requirements. This dynamic approach allows the system to reduce power consumption by adjusting control effort to match actual needs, while managing complexity through adaptive control algorithms that respond to changing conditions.
Data Source
AI summary
Controlling the pitch of individual rotor blades of a helicopter to reduce control loads, vibration and noise in or from the rotating rotor control elements. The system generates blade dynamics signals representing dynamic forces acting on either or both of the rotating and non-rotating elements of the helicopter, including rotor blades of a rotating assembly. The system extracts information representing at least one dynamic force, generates a dynamic force compensation output that represents a compensation for the dynamic force, and generates, from flight control signals and the dynamic force compensation output, a compensated pitch actuator control signal for each rotor blade wherein the compensation factor of the pitch control signal compensates for the dynamic force.