Method for monitoring the ageing of a landing gear of an aircraft
First Claim
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1. A method for monitoring the aging of a landing gear of an aircraft implemented by an autonomous measuring device mounted on said landing gear, said autonomous measuring device including:
- at least one sensor configured for measuring physical parameters relating to the aging of the landing gear and at least one sensor configured for detecting the position of the landing gear and the landing of the aircraft,a storage memory for storing measurements relating to the aging of the landing gear according to said measured physical parameters,said monitoring method comprising the following steps;
after a landing of the aircraft, a stand-by step (“
STAND-BY”
) comprising detecting with the aid of said sensors the position of the landing gear at a first sampling frequency as long as the position of the landing gear is detected as vertical,after detection of a horizontal position of the landing gear, a sleeping step (“
SLEEP”
) comprising detecting with the aid of said sensors of the position of the landing gear at least at a second sampling frequency, as long as the position of the landing gear is detected as horizontal,after detection of a vertical position of the landing gear, a measuring step (“
AWAKE”
) comprising acquiring with the aid of said sensors physical parameters relating to the aging of the landing gear and detection of a landing of the aircraft until a predetermined period has expired after a landing has been detected,said monitoring method further comprising storing (“
STORAGE”
) in said storage memory of measurements relating to the aging of the landing gear according to said measured physical parameters,whereinthe sensors comprise accelerometers capable of measuring the linear accelerations of the landing gear along three axes in three orthogonal directions,wherein during the measuring step (AWAKE), the steps acquiring and detecting are implemented at a third sampling frequency,said third sampling frequency being greater than the second sampling frequency, said second sampling frequency being greater than said first sampling frequency,said third frequency being adapted to a measurement, by the accelerometers, of the intensity of successive shocks during a landing, a shock felt being measured in three axes by the accelerometers for multiple successive bounces including the first shock of landing, the accelerometer measurement sequences being filtered through a filter for quantifying these shocks, giving a shock value per axis in g for each measured bounce,the intensities thus measured being converted into a number of aging cycles, by a correspondence table,each shock felt incrementing the number of aging cycles undergone by the equipment,the total cycles being summed for each axis,and wherein when the summed total cycles reaches a given threshold for an axis (MaxCycles (X, Y or Z)), an alert is triggered.
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Abstract
A method is provided. The method includes, after a landing of an aircraft, detecting by sensors the position of the landing gear at a first sampling frequency, while the position of the landing gear is detected as vertical. After detection of a horizontal position of the landing gear, detecting by the sensors the position of the landing gear at least at a second sampling frequency, while the position of the landing gear is detected as horizontal. After detection of a vertical position of the landing gear, acquiring by said sensors physical parameters relating to the ageing of the landing gear, and detecting a landing of the aircraft at a third sampling frequency until a predetermined period has expired. The third frequency is greater than the second frequency, which is greater than the first frequency. Measurements relating to the ageing are stored as a function of the measured physical parameters.
8 Citations
13 Claims
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1. A method for monitoring the aging of a landing gear of an aircraft implemented by an autonomous measuring device mounted on said landing gear, said autonomous measuring device including:
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at least one sensor configured for measuring physical parameters relating to the aging of the landing gear and at least one sensor configured for detecting the position of the landing gear and the landing of the aircraft, a storage memory for storing measurements relating to the aging of the landing gear according to said measured physical parameters, said monitoring method comprising the following steps; after a landing of the aircraft, a stand-by step (“
STAND-BY”
) comprising detecting with the aid of said sensors the position of the landing gear at a first sampling frequency as long as the position of the landing gear is detected as vertical,after detection of a horizontal position of the landing gear, a sleeping step (“
SLEEP”
) comprising detecting with the aid of said sensors of the position of the landing gear at least at a second sampling frequency, as long as the position of the landing gear is detected as horizontal,after detection of a vertical position of the landing gear, a measuring step (“
AWAKE”
) comprising acquiring with the aid of said sensors physical parameters relating to the aging of the landing gear and detection of a landing of the aircraft until a predetermined period has expired after a landing has been detected,said monitoring method further comprising storing (“
STORAGE”
) in said storage memory of measurements relating to the aging of the landing gear according to said measured physical parameters,wherein the sensors comprise accelerometers capable of measuring the linear accelerations of the landing gear along three axes in three orthogonal directions, wherein during the measuring step (AWAKE), the steps acquiring and detecting are implemented at a third sampling frequency, said third sampling frequency being greater than the second sampling frequency, said second sampling frequency being greater than said first sampling frequency, said third frequency being adapted to a measurement, by the accelerometers, of the intensity of successive shocks during a landing, a shock felt being measured in three axes by the accelerometers for multiple successive bounces including the first shock of landing, the accelerometer measurement sequences being filtered through a filter for quantifying these shocks, giving a shock value per axis in g for each measured bounce, the intensities thus measured being converted into a number of aging cycles, by a correspondence table, each shock felt incrementing the number of aging cycles undergone by the equipment, the total cycles being summed for each axis, and wherein when the summed total cycles reaches a given threshold for an axis (MaxCycles (X, Y or Z)), an alert is triggered. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A non-transitory computer readable storage medium storing computer program code which, when executed by a processor, causes the processor to perform a method comprising the following steps:
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after a landing of the aircraft, a stand-by step (“
STAND-BY”
) comprising detecting with the aid of at least one sensor comprising accelerometers capable of measuring the linear acceleration of the landing gear along three axes in three orthogonal directions, a position of a landing gear at a first sampling frequency as long as the position of the landing gear is detected as vertical,after detection of a horizontal position of the landing gear, a sleeping step (“
SLEEP”
) comprising detecting with the aid of the at least one sensor the position of the landing gear at least at a second sampling frequency, as long as the position of the landing gear is detected as horizontal,after detection of a vertical position of the landing gear, a measuring step (“
AWAKE”
) comprising acquiring with the aid of the at least one sensor physical parameters relating to the aging of the landing gear and detecting a landing of the aircraft until a predetermined period has expired after the landing has been detected,a storing step of storing (“
STORAGE”
) in a storage memory measurements relating to the aging of the landing gear according to said measured physical parameters,wherein during the measuring step (AWAKE), the steps acquiring and detecting are implemented at a third sampling frequency, the third sampling frequency being greater than the second sampling frequency, and the second sampling frequency being greater than the first sampling frequency, the third frequency being adapted to a measurement, by the accelerometers, of the intensity of successive shocks during a landing, a shock felt being measured in three axes by the accelerometers for multiple successive bounces including the first shock of landing, the accelerometer measurement sequences being filtered through a filter for quantifying the shocks, giving a shock value per axis in g for each measured bounce, the intensities thus measured being converted into a number of aging cycles, by a correspondence table, each shock felt incrementing the number of aging cycles undergone by the equipment, the total cycles being summed for each axis, and wherein when the summed total cycles reaches a given threshold for an axis (MaxCycles (X, Y or Z)), an alert is triggered.
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9. An autonomous measuring device configured for being mounted on a landing gear, the autonomous measuring device comprising:
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at least one sensor configured for measuring physical parameters relating to the aging of the landing gear and at least one sensor configured for detecting the position of the landing gear and the landing of the aircraft, a storage memory for storing measurements relating to the aging of the landing gear according to said measured physical parameters, said comprising accelerometers capable of measuring the linear accelerations of the landing gear along three axes in three orthogonal directions and being configured, once mounted on the landing gear, for implementing said steps of a monitoring method comprising the following steps; after a landing of the aircraft, a stand-by step (“
STAND-BY”
) comprising detecting with the aid of said sensors the position of the landing gear at a first sampling frequency as long as the position of the landing gear is detected as vertical,after detection of a horizontal position of the landing gear, a sleeping step (“
SLEEP”
) comprising detecting with the aid of said sensors of the position of the landing gear at least at a second sampling frequency, as long as the position of the landing gear is detected as horizontal,after detection of a vertical position of the landing gear, a measuring step (“
AWAKE”
) comprising acquiring with the aid of said sensors physical parameters relating to the aging of the landing gear and detecting a landing of the aircraft until a predetermined period has expired after a landing has been detected,said monitoring method further comprising storing (“
STORAGE”
) in said storage memory measurements relating to the aging of the landing gear according to said measured physical parameters,wherein the sensors comprise accelerometers capable of measuring the linear accelerations of the landing gear along three axes in three orthogonal directions, wherein during the measuring step (AWAKE), the steps acquiring and detecting are implemented at a third sampling frequency, said third sampling frequency being greater than the second sampling frequency, said second sampling frequency being greater than said first sampling frequency, said third frequency being adapted to a measurement, by the accelerometers, of the intensity of successive shocks during a landing, a shock felt being measured in three axes by the accelerometers for multiple successive bounces including the first shock of landing, the accelerometer measurement sequences being filtered through a filter for quantifying these shocks, giving a shock value per axis in g for each measured bounce, the intensities thus measured being converted into a number of aging cycles, by a correspondence table, each shock felt incrementing the number of aging cycles undergone by the equipment, the total cycles being summed for each axis, and wherein when the summed total cycles reaches a given threshold for an axis (MaxCycles (X, Y or Z)), an alert is triggered. - View Dependent Claims (10)
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11. A monitoring system comprising:
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an external terminal; and an autonomous measuring device configured for being mounted on a landing gear, the autonomous measuring device comprising; at least one sensor configured for measuring physical parameters relating to the aging of the landing gear and at least one sensor configured for detecting the position of the landing gear and the landing of the aircraft, a storage memory for storing measurements relating to the aging of the landing gear according to said measured physical parameters, said sensors comprising accelerometers capable of measuring the linear accelerations of the landing gear along three axes in three orthogonal directions and being configured, once mounted on the landing gear, for implementing said steps of a monitoring method comprising the following steps; after a landing of the aircraft, a stand-by step (“
STAND-BY”
) comprising detecting with the aid of said sensors the position of the landing gear at a first sampling frequency as long as the position of the landing gear is detected as vertical,after detection of a horizontal position of the landing gear, a sleeping step (“
SLEEP”
) comprising detecting with the aid of said sensors of the position of the landing gear at least at a second sampling frequency, as long as the position of the landing gear is detected as horizontal,after detection of a vertical position of the landing gear, a measuring step (“
AWAKE”
) comprising acquiring with the aid of said sensors physical parameters relating to the aging of the landing gear and detecting a landing of the aircraft until a predetermined period has expired after a landing has been detected,said monitoring method further comprising storing (“
STORAGE”
) in said storage memory measurements relating to the aging of the landing gear according to said measured physical parameters,wherein the sensors comprise accelerometers capable of measuring the linear accelerations of the landing gear along three axes in three orthogonal directions, wherein during the measuring step (AWAKE), the steps acquiring and detecting are implemented at a third sampling frequency, said third sampling frequency being greater than the second sampling frequency, said second sampling frequency being greater than said first sampling frequency, said third frequency being adapted to a measurement, by the accelerometers, of the intensity of successive shocks during a landing, a shock felt being measured in three axes by the accelerometers for multiple successive bounces including the first shock of landing, the accelerometer measurement sequences being filtered through a filter for quantifying these shocks, giving a shock value per axis in g for each measured bounce, the intensities thus measured being converted into a number of aging cycles, by a correspondence table, each shock felt incrementing the number of aging cycles undergone by the equipment, the total cycles being summed for each axis, and wherein when the summed total cycles reaches a given threshold for an axis (MaxCycles (X, Y or Z)), an alert is triggered, and wherein said autonomous measuring device further comprises a communication interface configured for transmitting to said external terminal the measurements relating to the aging of the landing gear stored in said storage memory. - View Dependent Claims (12, 13)
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Specification
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Current AssigneeSafran Electronics & Defense, Safran Landing Systems
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Original AssigneeSafran Electronics & Defense
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InventorsVinson, Garance, Fanton, Nicolas, Tine, Pierre-Jean, Vitry, Sully, Loustaudaudine, Christophe
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Primary Examiner(s)Troost, Aaron L
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Application NumberUS16/064,855Publication NumberTime in Patent Office1,050 DaysField of SearchUS Class CurrentCPC Class CodesB64D 2045/008 Devices for detecting or in...B64D 2045/0085 Devices for aircraft health...B64D 45/00 Aircraft indicators or prot...B64F 5/60 Testing or inspecting aircr...G07C 5/008 communicating information t...G07C 5/085 using electronic data carriersH04W 4/80 Services using short range ...
