Method for evaluating measured values for identifying a material fatigue
First Claim
1. Method for the evaluation of measured values for the recognition of defect conditions due to material fatigue on aircraft parts, in which strain sensors (6) are applied on the critical locations of an aircraft (1) or its parts, whereby the measured values of the strain sensors are detected at different loading conditions through several measuring circuits, are amplified, and are stored, and from which an evaluating apparatus (9) derives a material fatigue through comparison of current measured values with previous measured values and signals or indicates the material fatigue, characterized in that the critical aircraft parts (1) are impinged on with a plurality of prescribed loading conditions by a plurality of loading elements (3), and in that the strain effect caused thereby is detected through a plurality of measuring circuits, and the evaluating apparatus (9) for at least each load condition and each measuring circuit forms an allocated reference value and a permissible limit value range, which is subsequently coupled with the current measured values so that the exceeding of the limit value range represents a material fatigue manifestation.
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Accused Products
Abstract
The invention relates to a method for the evaluation of measured values for the recognition of defect conditions due to material fatigue on aircraft parts, in which strain sensors (6) are applied on the critical locations of an aircraft (1) or the parts thereof, wherein the measured values of the strain sensors at different loading conditions are detected, amplified and stored through several measuring circuits and from which an evaluating apparatus (9) derives, signals or indicates a material fatigue by comparison of current measured values with previous measured values. In that regard, the evaluating method is characterized in that the critical aircraft parts (1) are impinged on with a plurality of prescribed loading conditions by a plurality of loading elements (3), and in that the strain effect caused thereby is detected by a plurality of measuring circuits, and the evaluating apparatus (9) forms, for at least each loading condition and each measuring circuit, an allocated reference value and a permissible limit value range, which is subsequently coupled with the current measured values in such a manner so that the exceeding of the limit value range represents a material fatigue manifestation.
25 Citations
28 Claims
- 1. Method for the evaluation of measured values for the recognition of defect conditions due to material fatigue on aircraft parts, in which strain sensors (6) are applied on the critical locations of an aircraft (1) or its parts, whereby the measured values of the strain sensors are detected at different loading conditions through several measuring circuits, are amplified, and are stored, and from which an evaluating apparatus (9) derives a material fatigue through comparison of current measured values with previous measured values and signals or indicates the material fatigue, characterized in that the critical aircraft parts (1) are impinged on with a plurality of prescribed loading conditions by a plurality of loading elements (3), and in that the strain effect caused thereby is detected through a plurality of measuring circuits, and the evaluating apparatus (9) for at least each load condition and each measuring circuit forms an allocated reference value and a permissible limit value range, which is subsequently coupled with the current measured values so that the exceeding of the limit value range represents a material fatigue manifestation.
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3-15. -15. (canceled)
Specification