System and method for measuring fatigue for mechanical components of an aircraft and aircraft maintenance method
First Claim
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1. A system for measuring fatigue of an aircraft component subjected to mechanical stresses, the system comprising:
- a plurality of stress sensors Ci mounted on the aircraft component in which i=1 to n where n is a number of sensors, each sensor being configured to detect a predetermined mechanical stress threshold S(Ci) and to deliver a data signal representative of violation of this threshold;
means for recording the data signal; and
means for calculating damage based on the data signal,wherein the sensors are configured to detect different thresholds of a same stress, which thresholds are staged so as to compute, based on a number of threshold violation occurrences of each sensor n(Cn), an estimate of fatigue of the aircraft component due to the predetermined mechanical stress,wherein each sensor Ci measures a number of occurrences N(Ci) of stress higher than the stress threshold S(Ci), and the number of threshold violation occurrences n(Cn) between the stress threshold of the sensor S(Ci) and a higher stress threshold S(Ci+1) is computed as n(Cn)=N(Cn);
for i<
n, n(Ci)=N(Ci)−
N(Ci+1),wherein for each sensor Ci, an equivalent damage Di for the aircraft component corresponding to a range of stresses between the stress threshold S(Ci) of the sensor Ci and the higher threshold S(Ci+1) is computed, and the estimate of fatigue of the aircraft component is calculated based on a sum of the equivalent damage Di for each sensor Ci.
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Abstract
A system for measuring fatigue of a component of an aircraft subject to mechanical stresses includes: a plurality of stress sensors mounted on the component, each sensor being configured to detect a predetermined mechanical stress threshold and to deliver a data signal representative of exceeding of the threshold; and a mechanism for recording the data and the sensors configured to detect different stress thresholds so as to make it possible to calculate, on the basis of the data recorded by the system, an estimation of fatigue of the component due to the mechanical stresses. It is thus possible to optimize overhaul of the components.
105 Citations
12 Claims
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1. A system for measuring fatigue of an aircraft component subjected to mechanical stresses, the system comprising:
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a plurality of stress sensors Ci mounted on the aircraft component in which i=1 to n where n is a number of sensors, each sensor being configured to detect a predetermined mechanical stress threshold S(Ci) and to deliver a data signal representative of violation of this threshold; means for recording the data signal; and means for calculating damage based on the data signal, wherein the sensors are configured to detect different thresholds of a same stress, which thresholds are staged so as to compute, based on a number of threshold violation occurrences of each sensor n(Cn), an estimate of fatigue of the aircraft component due to the predetermined mechanical stress, wherein each sensor Ci measures a number of occurrences N(Ci) of stress higher than the stress threshold S(Ci), and the number of threshold violation occurrences n(Cn) between the stress threshold of the sensor S(Ci) and a higher stress threshold S(Ci+1) is computed as n(Cn)=N(Cn);
for i<
n, n(Ci)=N(Ci)−
N(Ci+1),wherein for each sensor Ci, an equivalent damage Di for the aircraft component corresponding to a range of stresses between the stress threshold S(Ci) of the sensor Ci and the higher threshold S(Ci+1) is computed, and the estimate of fatigue of the aircraft component is calculated based on a sum of the equivalent damage Di for each sensor Ci. - View Dependent Claims (2, 3, 4, 5, 9, 10, 11)
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6. A method for measuring fatigue of an aircraft component subjected to a predetermined mechanical stress, comprising:
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placing a plurality of sensors Ci capable of detecting predetermined thresholds of the predetermined mechanical stress S(Ci) on the aircraft component in which i=1 to n where n is a number of sensors, the sensors being staged relative to one another and each being capable of delivering a data signal representative of violation of its threshold S(Ci) by the stress; measuring the stress on the aircraft component using the plurality of sensors Ci; recording a number of occurrences N(Ci) of measurements of violation of the threshold S(Ci) for each sensor Ci; computing using a computer, for each sensor, a number of threshold violation occurrences n(Cn) between the stress threshold of the sensor S(Ci) and a higher threshold S(Ci+1) as n(Cn)=N(Cn);
for i<
n, n(Ci)=N(Ci)−
N(Ci+1); andcomputing, based on the number of occurrences, an estimate of fatigue of the aircraft component caused by the predetermined mechanical stress by computing, for each sensor, an equivalent damage Di for the aircraft component corresponding to a range of stresses between the stress threshold S(Ci) of the sensor Ci and the higher threshold S(Ci+1) and summing the equivalent damage Di for each sensor Ci. - View Dependent Claims (7, 8, 12)
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Specification
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Current AssigneeSafran Aircraft Engine Company
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Original AssigneeSnecma (Safran SA)
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InventorsSeize, Guilhem
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Primary Examiner(s)Algahaim, Helal A
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Assistant Examiner(s)WAGNER, REBECCA A
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Application NumberUS13/509,874Publication NumberTime in Patent Office1,114 DaysField of SearchNoneUS Class Current701/33.2CPC Class CodesG01M 5/0033 by determining damage, crac...G01N 2203/0073 FatigueG01N 2203/0286 Miniature specimen; Testing...G01N 3/32 by applying repeated or pul...G07C 5/006 Indicating maintenanceG07C 5/0841 Registering performance dat...
