Aircraft Active Vibration Control Actuator Mounting Bracket
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Solution Overview
Problem
Existing active vibration control systems in aircraft face challenges with easy installation and removal of actuators and brackets, particularly in retrofit applications, which hinders efficient noise and vibration suppression.
Innovation Solution
The implementation of dynamically tuned actuator mounting brackets that allow for unhindered access and minimal modifications to the aircraft structure, enabling easy installation and removal of actuators while effectively suppressing vibrations and noise through a system of sensors and controllers that control a limited number of actuators based on feedback signals.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional actuator mounting brackets are used, then the structural strength is maintained, but the installation and removal of actuators becomes difficult and time-consuming
Solution Approach 1:
The mounting bracket is divided into a stationary portion attached to the aircraft structure and a movable portion that can be easily attached and detached from the actuator. This segmentation allows the actuator to be quickly installed and removed without modifying the bracket structure, resolving the contradiction between ease of operation and device complexity.
Solution Approach 2:
The bracket incorporates movable elements such as adjustable arms or repositionable mounting points that can be dynamically adjusted during installation and removal operations. This dynamic capability enables easy actuator exchange while maintaining structural integrity, addressing the contradiction between operational ease and design complexity.
2Reliability
If multiple actuators are installed for each engine, then the vibration and sound suppression effectiveness is improved, but the system weight and complexity increase
Solution Approach 1:
Instead of installing actuators at all potential mounting locations, the system strategically positions a minimal number of actuators (no more than two per engine) at optimally selected locations that provide maximum vibration suppression effectiveness. This partial action approach achieves the required reliability while minimizing system weight and complexity.
Solution Approach 2:
The system optimizes actuator placement by varying positional parameters and operational parameters to achieve effective vibration suppression with fewer actuators. By carefully selecting actuator locations and control parameters, the system maintains high reliability while reducing the number of actuators needed, thereby decreasing weight and complexity.
3Stability of the object's composition
If actuators are firmly secured to the aircraft structure, then the structural stability is maintained, but the retrofit installation becomes more difficult
Solution Approach 1:
The mounting system is segmented into a permanent stationary bracket portion that maintains structural stability and a removable actuator portion that enables easy retrofit installation. The stationary portion is firmly attached to the aircraft structure, while the movable portion allows simple actuator exchange without structural modifications, resolving the contradiction between stability and ease of manufacture.
Solution Approach 2:
The mounting bracket serves as an intermediary element between the aircraft structure and the actuator. It provides stable structural attachment points while incorporating flexible mounting mechanisms that facilitate easy actuator installation and removal, effectively mediating between the requirements for structural stability and retrofit ease.
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 provides effective noise and vibration suppression, improving ride comfort and reducing engine-related disturbances with minimal additional weight and complexity, allowing for efficient retrofitting of active vibration control systems to existing aircraft.
Implementation Method 1
use shakers or actuators (e.g. active vibration elements) to vibrate a structural component at a discrete frequency to cancel the input disturbance
Implementation Method 2
vibrate a structural component at a discrete frequency
Implementation Method 3
detect a magnitude and frequency of one or more of vibration and sound produced by a respective engine
Data Source
Figure 1A~1B
Figure 1C
Figure 1D
AI summary
An active vibration control system (110) includes a plurality of actuators (150-155) corresponding to and disposed adjacent each engine (102) of an aircraft (100), at least one sensor (650) located within a passenger cabin (100C) of the aircraft (100) and configured to detect a magnitude and frequency of one or more of vibration and sound produced by a respective engine (102) and generate one or more of a vibration and sound feedback signal, and a controller (500) connected to each of the plurality of actuators (150-155) and each of the at least one sensor (650), the controller (500) being configured to effect control of no more than two of the plurality of actuators (150-155) for a respective engine (102) based the feedback signal where the no more than two actuators (150-155) effect suppression of one or more of vibration and sound of a respective engine due to rotating axis of the respective engine (102).