Aircraft High Lift System Component State Monitoring
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Solution Overview
Problem
High lift systems in aircraft face challenges in accurately monitoring component states without increasing sensor accuracy, which leads to higher development and manufacturing costs, and existing methods are not robust enough to handle increased stiffness of flaps and aerodynamic surfaces.
Innovation Solution
A method that involves acquiring and comparing positional data from sensors on the ground and in flight to determine deviations, generating a signal for abnormal states, allowing for reduced sensor accuracy while maintaining robustness and reliability, by using standard sensor accuracies and electronic calibration to eliminate systematic errors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If sensor accuracy is increased to maintain monitoring robustness with increased flap stiffness, then measurement precision is improved, but manufacturing cost increases
Solution Approach 1:
The system performs preliminary calibration measurements on the ground before flight to establish reference values for sensor positions. This preliminary action allows the system to account for manufacturing tolerances and installation variations, enabling the use of standard-accuracy sensors while maintaining monitoring robustness through comparative analysis between ground calibration data and in-flight measurements.
2Reliability
If skew threshold is reduced to detect attachment disconnections with stiffer flaps, then reliability is improved, but measurement precision requirements increase
Solution Approach 1:
The system uses feedback from ground-based calibration measurements to establish reference position values for each sensor. During flight, the system compares real-time sensor readings against these calibrated reference values, compensating for reduced skew thresholds and enabling reliable detection of attachment disconnections using standard-accuracy sensors rather than requiring high-precision sensors.
Solution Approach 2:
The system changes the measurement parameter from absolute position monitoring to differential position monitoring by comparing in-flight sensor readings with ground-calibrated reference values. This parameter transformation allows the system to detect abnormal states with standard-accuracy sensors even when skew effects are minimized due to increased flap stiffness.
3Ease of manufacture
If standard sensor accuracy is used to reduce manufacturing costs, then ease of manufacture is improved, but measurement precision decreases
Solution Approach 1:
The system introduces ground-based calibration measurements as an intermediary process that mediates between standard-accuracy sensors and the requirement for reliable monitoring. The calibration process captures the actual position of each sensor in the ground configuration, creating reference values that compensate for sensor inaccuracies. This intermediary calibration step enables the system to achieve reliable monitoring functionality using cost-effective standard-accuracy sensors.
Data Source
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AI summary
A method for determining a state of a component in a high lift system (2) of an aircraft is proposed, the high lift system (2) comprising a central power control unit (4) for providing rotational power by means of a transmission shaft (8, 10); and drive stations (12) coupled with the power control unit (4) and movable high lift surfaces (18); the method comprising the steps of acquiring in an extended position in flight at least one first position of a first position pick-off unit (20) coupled with the component, which is mechanically coupled with one of the high lift surfaces (18), and which is coupled with one of the drive stations (12), acquiring on ground at least one second position of the first position pick-off unit (20) in the extended position, determining a deviation between a measure based on the first position and an associated measure based on the second position of the first position pick-off unit (20) between ground and flight, determining, whether the deviation exceeds a predetermined threshold and generating a signal indicating an abnormal state of the component in case the deviation exceeds the predetermined threshold.