Incorrect Force Mitigation System for Aircraft Vibration Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Active Vibration Control (AVC) systems on aircraft can reduce the life of structural components and fail to detect incorrect forces that may cause damage, lacking integrated structural health monitoring and protection capabilities.
Innovation Solution
An Incorrect Force Mitigation System (IFMS) that combines an Active Vibration Control (AVC) system with a Structural Health Monitoring (SHM) system, using sensors and controllers to detect and mitigate incorrect forces by adjusting force commands and communicating bi-directionally to prevent damage to aircraft structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If an AVC system uses force generators to reduce vibration, then vibration reduction is achieved, but incorrect forces may be applied causing structural damage
Solution Approach 1:
The patent implements a feedback mechanism where structural health sensors continuously monitor structural parameters (acceleration, strain, stress) and provide real-time data to the controller. The controller compares actual structural response with expected response and adjusts force generator commands to correct deviations, preventing incorrect forces from causing structural damage while maintaining vibration reduction effectiveness
Solution Approach 2:
The patent introduces structural health sensors and a monitoring controller as intermediary elements between the force generators and the structure. These intermediaries detect structural health parameters and mediate the control signals to ensure force generators apply correct forces, thereby preventing structural damage while achieving vibration reduction
2Device complexity
If an AVC system operates without structural health monitoring, then system simplicity is maintained, but incorrect forces cannot be detected or mitigated
Solution Approach 1:
The patent makes the controller multi-functional by enabling it to perform both AVC control functions (generating force commands for vibration reduction) and structural health monitoring functions (processing sensor data, detecting incorrect forces, mitigating structural risks). This integration allows the system to gain detection and protection capabilities without proportionally increasing overall system complexity
Solution Approach 2:
The patent merges the AVC control system and structural health monitoring system into a unified integrated system. The force generators, structural health sensors, and controller are combined such that the same controller manages both vibration control and structural protection, reducing the need for separate independent systems and minimizing overall complexity while achieving both functions
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 IFMS effectively extends the life of aircraft structures by detecting and mitigating incorrect forces, reducing vibration and stress, and providing predictive maintenance through integrated health monitoring and protection.
Implementation Method 1
Active Vibration Control (AVC) systems on aircraft and other mechanical structures use various types of force generators (FGs). These FGs are used to produce vibratory loads for the purposes of reducing vibration based on accelerometer feedback.
Implementation Method 2
a Structural Health Monitoring (SHM) system comprising at least one structural health sensor configured to measure a structural load, a strain, or a vibration
Data Source
Figure 1A
Figure 1B
Figure 2
AI summary
Structural health monitoring and protection systems and methods are provided. System and methods utilize structural information and/or enhanced built in testing capabilities for detecting failure modes that may cause damage to a structure. Systems and methods herein may protect a structure by mitigating one or more incorrect forces. The structure may be an aircraft, a rotary wing aircraft, or any other physical structure subject to vibrations and receptive to canceling of those vibrations.