METHOD AND APPARATUS FOR MEASURING THE STRUCTURAL INTEGRITY OF A SAFE-LIFE AIRCRAFT COMPONENT
First Claim
1. A method of measuring the structural integrity of a safe-life aircraft component on an aircraft, the component comprising a load-bearing metal element that is free from cracks, the method including the steps of:
- converting acoustic emissions generated in the metal element into electronic signals, the acoustic emissions converted including relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks,sending the electronic signals to a processing unit, andwith the processing unit processing over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made from the signals sent to the processing unit, andoutputting information providing a measure of the structural integrity of the aircraft component before any cracks occur.
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Accused Products
Abstract
The structural integrity of a safe-life aircraft component on an aircraft is measured and assessed by a processing unit. The component includes a load-bearing metal element that is free from cracks. In the method, acoustic emissions generated in the metal element are converted into electronic signals. The acoustic emissions converted include relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks. The electronic signals are set to a processing unit. The processing unit processes over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made. Information providing a measure of the structural integrity of the aircraft component is outputted. Thus, deterioration of the structure of the component can be detected and monitored before a crack occurs.
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Citations
44 Claims
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1. A method of measuring the structural integrity of a safe-life aircraft component on an aircraft, the component comprising a load-bearing metal element that is free from cracks, the method including the steps of:
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converting acoustic emissions generated in the metal element into electronic signals, the acoustic emissions converted including relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks, sending the electronic signals to a processing unit, and with the processing unit processing over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made from the signals sent to the processing unit, and outputting information providing a measure of the structural integrity of the aircraft component before any cracks occur. - View Dependent Claims (2, 3, 4, 5, 6, 14, 20, 21, 22, 23, 24, 25, 26, 28, 31, 33, 35, 36, 37, 39, 41, 42, 43, 44)
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7-13. -13. (canceled)
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15-19. -19. (canceled)
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27. (canceled)
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29. A method of acquiring data for subsequent processing, the data concerning the structural properties of a safe-life aircraft component on an aircraft, the component comprising a load-bearing metal element that is free from cracks, the method comprising:
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converting acoustic emissions generated in the metal element into electronic signals, the acoustic emissions converted including relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks, assessing which of the electronic signals correspond to relevant acoustic emissions, and storing the electronic signals that have been assessed as corresponding to relevant acoustic emissions as measurement data in a data storage. - View Dependent Claims (38, 40)
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30. A method of measuring the structural integrity of a safe-life aircraft component on an aircraft, the component comprising a load-bearing metal element, the method comprising the steps of:
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arranging at least one acoustic emission sensor on or around the metal element that is free from cracks, acquiring, by the at least one acoustic emission sensor, measurement data, including data concerning relevant acoustic emissions generated in the metal element as a result of changes in the submicrostructure of the metal element that contribute to the formation of cracks and make the element more susceptible to the formation of cracks, processing the data so acquired with a processing unit in conjunction with stored reference data that allows a measure of the structural integrity of the aircraft component to be made from the acquired measurement data, and outputting information providing a measure of the structural integrity of the aircraft component before any cracks occur. - View Dependent Claims (32, 34)
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Specification