Aircraft Actuator Damage Monitoring via Integrated Sensors
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Solution Overview
Problem
Current methods for monitoring flight control actuators in aircraft are theoretical and lack real-time data, leading to difficulties in determining actual life potential and predicting failure, resulting in conservative usage and increased maintenance costs.
Innovation Solution
A system with sensors and processing means integrated into the actuator to collect and calculate damage indicators, providing real-time data on stress and life potential, and storing this information in a non-volatile memory for traceability and diagnostics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If theoretical qualification methods are used to determine actuator life, then safety is ensured through conservative estimates, but the duration of use is significantly limited and maintenance costs increase
Solution Approach 1:
The system performs preliminary damage assessment during normal operation by continuously monitoring actuator parameters and accumulating damage indicators before actual failure occurs. This allows for proactive maintenance scheduling based on real damage accumulation rather than conservative theoretical limits.
Solution Approach 2:
The monitoring system provides continuous feedback on actual actuator condition through damage indicators derived from sensor data. This feedback loop enables dynamic adjustment of maintenance schedules and extends actuator usage beyond theoretical limits by confirming actual condition matches or exceeds predicted performance.
2Ease of manufacture
If theoretical qualification methods are used for actuator life assessment, then fleet-wide conservative limits can be applied, but significant limitations are placed on actuator usage duration and maintenance flexibility
Solution Approach 1:
The system transitions from fixed theoretical life parameters to dynamic damage indicator parameters that change based on actual operating conditions. Multiple damage indicators (fatigue, endurance, thermal) are calculated and combined to provide a comprehensive view of actuator health, enabling flexible maintenance scheduling.
3Loss of information
If data is stored externally to the actuator, then access is easier, but information regarding actuator use may be lost during repairs and reinstallation
Solution Approach 1:
The monitoring system embeds a non-volatile memory unit directly within the actuator assembly, creating a nested structure where data storage is integrated into the component itself. This ensures damage indicators and operational data are permanently attached to the actuator and cannot be lost during removal, repair, or reinstallation.
4Reliability
If conservative fleet-wide limits are applied to all actuators, then safety is maintained across the fleet, but the duration of use is limited and availability decreases
Solution Approach 1:
The system applies local quality assessment by evaluating each actuator's actual condition through dedicated sensors and damage indicators specific to that component's operational history and stress exposure. This replaces uniform fleet-wide limits with individualized assessments, allowing each actuator to operate up to its actual capabilities.
Data Source
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AI summary
The invention relates to a monitoring system for a flight control actuator of an aircraft, comprising: - an actuator (1), - sensors (3a-3d) at the actuator (1) to collect, at each flight of the aircraft, series of measurements on parameters relating to said actuator, - processing means (5) to calculate a set of damage indicators by cumulatively using the series of measurements observed during each of the successive flights of the aircraft, and - a memory (7; 7a) to store said set of damage indicators, said memory being integrated in the actuator.