Rotorcraft structural fault-detection and isolation using virtual monitoring of loads

Patent metadata

Field	Value
Publication number	US-2018165898-A1
Application number	US-201615748001-A
Country	US
Kind code	A1
Filing date	Jul 27, 2016
Priority date	Aug 4, 2015
Publication date	Jun 14, 2018
Grant date	—

Abstract

A system, method, and computer program for detecting and isolating structural faults is provided. To detect and isolate structural faults, a plurality of sensed features that corresponds to sensor data from the monitoring sub-system and a plurality of estimated features that corresponds to the plurality of sensed features can be generated. Further, the plurality of sensed features and the plurality of estimated features can be compared to produce a plurality of residuals. From the plurality of residuals, at least one structural fault within the vehicle are determined and isolated for further use of maintenance decision support.

First claim

1 . A method for detection and isolation of at least one structural fault, comprising:
generating, by a computing device communicatively coupled to a monitoring sub-system that is physically coupled to a vehicle, a plurality of sensed features that corresponds to sensor data from the monitoring sub-system; generating based on a model, by the computing device, a plurality of estimated features that corresponds to the plurality of sensed features; comparing, by the computing device, the plurality of sensed features and the plurality of estimated features to produce a plurality of residuals; determining, by the computing device, from the plurality of residuals whether the at least one structural fault exists within the vehicle; and isolating, by the computing device, the at least one structural fault from the plurality of residuals.

2 . The method of claim 1 , further comprising:
receiving, by the computing device from the monitoring sub-system, the sensor data, the sensor data being detected by at least one sensor of the monitoring sub-system, the at least one sensor being physically coupled to the vehicle.

3 . The method of claim 1 , the generating of the plurality of estimated features based on the model further comprising:
receiving by the computing device stored sensor information; processing the stored sensor information in accordance with the model to produce estimated data; and processing, via signal processing techniques, the estimated data to produce the plurality of estimated features.

4 . The method of claim 1 , wherein the sensor data includes low-frequency state parametric data or high frequency state parametric data.

5 . The method of claim 1 , wherein each residual includes a magnitude and polarity that are utilized with respect to a threshold range during the determining of whether the at least one structural fault exists.

6 . The method of claim 1 , wherein the computing device is a ground based device.

7 . The method of claim 1 , wherein the vehicle is an aircraft.

8 . The method of claim 7 , wherein the computing device is integral to the aircraft.

9 . A structural diagnostic system, comprising a processor and a memory having program instructions for detection and isolation of at least one structural fault embodied therewith, the program instructions executable by the processor to cause:
generating, by the processor communicatively coupled to a monitoring sub-system that is physically coupled to a vehicle, a plurality of sensed features that corresponds to sensor data from the monitoring sub-system; generating based on a model, by the processor, a plurality of estimated features that corresponds to the plurality of sensed features; comparing, by the processor, the plurality of sensor features and the plurality of estimated features to produce a plurality of residuals; determining, by the processor, from the plurality of residuals whether the at least one structural fault exists within the vehicle; and isolating, by the processor, the at least one structural fault from the plurality of residuals.

10 . The structural diagnostic system of claim 9 , wherein the program instructions are further executable by the processor to cause:
receiving by the processor from the monitoring sub-system the sensor data from the monitoring sub-system, the sensor data being detected by at least one sensor of the monitoring sub-system, the at least one sensor being physically coupled to the vehicle.

11 . The structural diagnostic system of claim 9 , wherein, with respect to the generating of the plurality of estimated features based on the model, the program instructions are further executable by the processor to cause:
receiving by the processor stored sensor information; processing the stored sensor information in accordance with the model to produce estimated data; and processing via signal processing techniques the estimated data to produce the plurality of estimated features.

12 . The structural diagnostic system of claim 9 , wherein the sensor data includes low-frequency state parametric data or high frequency state parametric data.

13 . The structural diagnostic system of claim 9 , wherein each residual includes a magnitude and polarity that are utilized with respect to a threshold range during the determining of whether the at least one structural fault exists.

14 . The structural diagnostic system of claim 9 , wherein the computing device is a ground based device.

15 . The structural diagnostic system of claim 9 , wherein the vehicle is an aircraft.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Isom Joshua D
• Davis Mark W
• Cycon James Peter

Classifications

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title

• B64C27/04

  Helicopters · CPC title

• G07C5/0825 Primary

  using optical means · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title