PATENT CLAIM ANALYSIS

Application Number: 16064855
Application Type: Utility
Filing Date: 2018-06
Publication Date: 2019-01
Patent Classification: ["701", "031500"]

Abstract:
The present invention relates to a method for monitoring the ageing of a landing gear of an aircraft, implemented by an autonomous measurement device installed on said landing gear and comprising sensors and a memory for storage, and comprising: after a landing of the aircraft, a stand-by step comprising detection by means of said sensors of the position of the landing gear at a first sampling frequency, for as long as the position of the landing gear is detected as vertical; after detection of a horizontal position of the landing gear, a sleep step comprising detection by means of said sensors of the position of the landing gear at least at a second sampling frequency, for as long as the position of the landing gear is detected as horizontal; after detection of a vertical position of the landing gear, a measurement step comprising acquisition by means of said sensors of physical parameters relating to the ageing of the landing gear, and detection of a landing of the aircraft at a third sampling frequency until a predetermined period has expired after a landing has been detected, said third frequency being greater than said second frequencies, and said second frequencies being greater than said first frequency; and storage in said storage memory of measurements relating to the ageing of the landing gear as a function of the measured physical parameters.

Claim (Index 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 and comprising:\n 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:\n after a landing of the aircraft, a stand-by step (\u201cSTAND-BY\u201d) comprising detection with the aid of said sensors of the position of the landing gear at a first sampling frequency as long as the position of the landing gear is detected as vertical, \n after detection of a horizontal position of the landing gear, a sleep step (\u201cSLEEP\u201d) comprising detection 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, \n after detection of a vertical position of the landing gear, a measuring step (\u201cAWAKE\u201d) comprising acquisition with the aid of said sensors of 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, \n said monitoring method further comprising a storage (\u201cSTORAGE\u201d) 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 acquisition and detection are implemented at a third sampling frequency, this frequency being greater than the second sampling frequency or frequencies, said second frequency or frequencies being greater than said first frequency/frequencies, 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 number of aging cycles, by a correspondence table, each shock felt incrementing the number of cycles undergone by the equipment, the total cycles being summed for each axis, and wherein when the number of cycles reaches a given threshold for the axis in question (Max Cycles (X, Y or Z) ), an alert is triggered.

Metadata:
- Claim Count in Document: 8.0
- Percentile: 94.0
- Lexical Diversity: 3.42254
- Patent Class: 701.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: True
- Related Applications: ['12123891', '11225602', '12469976', '11092020', '11560451']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.4044438668222125
- 35 USC 102 Novelty (BERT): 0.4879935345259569
- Combined Prediction Score: 0.4127988335925869
- Mean Citation Score: 217.64604
- Max Citation Score: 222.05849
- Similarity Product: 168.06533968838215

Labels:
- Claim Label 101: 1
- Claim Label 102: 1
- Claim Label 103: 1
- Claim Label 112: 1
- Combined Label: 1
- Label 101 Adjusted: 0

Dataset: test