Active Vibration Control Using Real-Time Avionics Data
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Solution Overview
Problem
Conventional active vibration control systems for aircraft fail to account for real-time changes in aircraft information such as airspeed, rotor speed, and altitude, leading to inefficient vibration control, especially during transient and steady-state conditions.
Innovation Solution
An active vibration control method that adjusts control parameters in real-time using data from avionics systems, including sensors and actuators, to generate force commands that counteract rotor-induced vibrations, improving both steady-state and transient performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If passive vibration control devices are used, then vibration control is achieved, but aircraft weight increases significantly
Solution Approach 1:
The patent replaces passive mechanical vibration control devices with an active control system that uses sensors, processors, and actuators. The system electronically generates control forces based on real-time vibration measurements and aircraft operating conditions, eliminating the need for heavy passive mechanical dampers while achieving superior vibration reduction across varying flight conditions.
Solution Approach 2:
The patent implements a dynamic control system that continuously adapts control parameters based on real-time aircraft information including forward air speed, rotor speed, and altitude. This dynamic adjustment allows the system to maintain optimal vibration control performance across different operating conditions without requiring heavy passive devices tuned for specific frequencies.
2Object-affected harmful factors
If conventional active vibration control systems are used, then vibration control is provided, but the system fails to adapt to real-time changes in aircraft operating conditions
Solution Approach 1:
The patent implements a feedback control system that continuously monitors vibration levels and aircraft operating conditions (forward air speed, rotor speed, altitude) and adjusts control parameters in real-time. The processor receives sensor data, updates control parameters based on current operating conditions, and generates appropriate control forces, creating a closed-loop system that adapts to changing flight conditions.
Solution Approach 2:
The patent changes control parameters dynamically based on aircraft operating conditions. The system adjusts control forces and frequencies according to real-time data including forward air speed, rotor speed, and altitude, allowing optimal vibration control performance across different steady-state and transient operating conditions rather than relying on fixed parameters.
3Object-affected harmful factors
If active vibration control systems with real-time parameter adjustment are implemented, then vibration control effectiveness improves, but device complexity increases
Solution Approach 1:
The patent integrates multiple functions into a single control system that simultaneously processes vibration sensor data, monitors aircraft operating conditions (airspeed, rotor speed, altitude), updates control parameters, and generates control forces. This multi-functional approach consolidates what would otherwise require separate systems, managing complexity while achieving superior adaptive vibration control.
Data Source
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AI summary
Improved active vibration control (AVC) devices (20), systems, and related methods are provided herein. An AVC device (20) includes a controller (24) adapted to receive real-time aircraft information and adjust at least one control parameter as a function of the real-time aircraft information is provided. An AVC device is adapted to detect changes in real-time aircraft information, as the aircraft moves from a steady state to transient performance, low and high air speeds, or vice versa. An AVC system (e.g., AVCS) includes one or more sensors (22), one or more actuators (26), and a controller (24) adapted to receive real-time aircraft information and adjust at least one control parameter. In some aspects, a method of controlling vibration within an aircraft includes receiving vibration information from at least one sensor (22), receiving real-time aircraft information from an avionics system (40), adjusting at least one control parameter used in a control algorithm, and generating a force command.