Autonomous Acoustic Modules for Composite Impact Detection
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Solution Overview
Problem
Conventional non-destructive testing methods for composite material structures in aircraft are lengthy, inadequate for detecting internal damage, and require integration into aircraft design, limiting their use on existing aircraft and failing to detect impacts during flight.
Innovation Solution
A device comprising autonomous acoustic modules with remote communication capabilities, powered by micro-kinetic generators, allowing for remote data collection and analysis of sound waves to detect and evaluate impacts on composite material structures, enabling detection during flight without the need for wired connections or integration into aircraft design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional ultrasound-based checking is used to detect internal damage, then damage detection capability is improved, but the checking operation becomes lengthy and tedious
Solution Approach 1:
The patent applies preliminary action by embedding acoustic sensors and recording means within the composite material structure during manufacturing. This allows impact events to be recorded automatically as they occur, eliminating the need for lengthy post-manufacturing ultrasound inspections. The damage detection is performed continuously in real-time rather than through periodic manual checking.
Solution Approach 2:
The patent replaces the mechanical ultrasound-based inspection system with an acoustic sensor network embedded within the structure. Instead of using external ultrasound probes that require manual movement and complex operation, the system uses internal acoustic sensors that automatically detect and record impact events, significantly reducing inspection time while maintaining damage detection capability.
2Reliability
If additional plies are added to guarantee resilience against undetected defects, then structural reliability is improved, but aircraft weight increases and performance is penalized
Solution Approach 1:
The patent replaces the mechanical approach of adding redundant structural plies with an acoustic monitoring system. Instead of over-engineering the structure with additional weight-bearing layers to compensate for undetected defects, the system uses embedded acoustic sensors to detect and monitor impact events, allowing for targeted maintenance only when necessary, thereby maintaining reliability without the penalty of increased weight.
3Measurement precision
If wired sensor systems are used for impact detection, then detection capability is improved, but integration into existing aircraft becomes complex and time-consuming
Solution Approach 1:
The patent extracts the processing and communication functions from the embedded acoustic sensors, allowing the sensors to operate autonomously with local recording and wireless communication capabilities. This modular approach separates the sensing function (embedded in structure) from the processing function (external), enabling easy integration into existing aircraft without complex wiring modifications to the airframe.
Solution Approach 2:
The patent applies self-service by equipping each acoustic sensor with local recording means and wireless communication capabilities. The sensors autonomously detect, record, and transmit impact data without requiring external wiring or processing infrastructure, significantly simplifying integration into existing aircraft while maintaining high impact detection capability.
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
Facilitates efficient and remote monitoring of aircraft structures, allowing for timely detection and evaluation of impact criticality, reducing maintenance time and weight penalties associated with conventional methods.
Implementation Method 1
an array of sensors of the piezoelectric type installed around this opening on the internal face of the fuselage, and able to sense mechanical vibrations propagating in the structure of the fuselage around the opening and to produce electrical signals representative of the mechanical vibrations sensed
Implementation Method 2
electrical energy generating means, means for recording the sound waves sensed by its acoustic sensor
Data Source
AI summary
A device for detecting an impact on a composite material structure. This detection device comprises at least two acoustic modules intended to be secured to the composite material structure and a processing unit able to communicate remotely with each of the acoustic modules. Each acoustic module is electrically autonomous and comprises its own means for recording the sound waves sensed by its acoustic sensor. An aircraft structure is also provided comprising a composite material structural element equipped with the impact detection device. A method is also provided for detecting an impact on a composite material aircraft structural element equipped with an impact detection device.