DIAGNOSIS OF DRIVE SHAFT DISC COUPLINGS

• US 20170089805A1
• Filed: 03/31/2015
• Published: 03/30/2017
• Est. Priority Date: 06/02/2014
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Sheldon, Jeremy, Watson, Matthew James, Steele, Jeffrey, Kasper, David, Sarlashkar, Avinash, Davis, Mark W.
• Granted Patent: US 10,190,942 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: G01M 13/02 Gearings; Transmission mechanisms
• CPC Class Codes: G01M 13/028 Acoustic or vibration analysis
• CPC Class Codes: G01M 17/00 Testing of vehicles testing fluid tightness G01M3/00; testing elastic properties of bodies or chassis, e.g. torsion-testing, G01M5/00; testing alignment of vehicle headlight devices G01M11/06; testing of engines G01M15/00

Abstract

Embodiments are directed to obtaining data based on samples of a vibration signal, processing, by at least one processor, the data to obtain a qualitative and quantitative assessment of a health of the one or more components based on an application of the data to at least one model, and outputting the assessment. Embodiments of the disclosure may be applied to one or more components of a drive shaft of an aircraft.

Claims

1. A method applied to one or more components of a drive shaft of an aircraft, the method comprising:

obtaining data based on samples of a vibration signal;

processing, by at least one processor, the data to obtain a qualitative and quantitative assessment of a health of the one or more components based on an application of the data to at least one model; and

outputting the assessment.

2. The method of claim 1, wherein the obtained data is based on samples of drive shaft speed and torque.

3. The method of claim 1, further comprising:

segmenting the vibration signal into a plurality of segments representative of a revolution of the drive shaft based on a nominal speed of the drive shaft as part of processing the data.

4. The method of claim 3, further comprising:

resampling the vibration signal segments from constant time based sampling to constant angular based sampling.

5. The method of claim 4, further comprising:

averaging the resampled segments as part of processing the data.

6. The method of claim 5, further comprising:

converting the averaged resampled segments from a time domain signal representation to a frequency domain signal representation as part of processing the data.

7. The method of claim 6, further comprising:

extracting magnitudes from the frequency domain signal representation at frequencies representing integer multiples of a speed of the drive shaft as part of processing the data.

8. The method of claim 7, further comprising:

comparing the magnitudes to thresholds established for a healthy drive shaft; and

scheduling at least one of an inspection and a maintenance activity when the comparison indicates that the drive shaft is unhealthy.

9. The method of claim 1, wherein the health of the one or more components pertains to at least one of:

coupling cracking, disc buckling, bolt-hole elongation, corrosion, damage, security, wear, lamination spread, and loss of bolt preload in disc-style couplings.

10. An apparatus for use in connection with an aircraft, the apparatus comprising:

at least one processor; and

memory having instructions stored thereon that, when executed by the at least one processor, cause the apparatus to;

obtain data based on samples of a vibration signal;

process the data to obtain a qualitative and quantitative assessment of a health of one or more components of a drive shaft of the aircraft based on an application of the data to at least one model; and

output the assessment.

11. The apparatus of claim 10, wherein the instructions, when executed by the at least one processor, cause the apparatus to:

segment the vibration signal into a plurality of segments representative of a revolution of the drive shaft based on a nominal speed of the drive shaft as part of processing the data.

12. The apparatus of claim 11, wherein the instructions, when executed by the at least one processor, cause the apparatus to:

average the segments as part of processing the data.

13. The apparatus of claim 12, wherein the instructions, when executed by the at least one processor, cause the apparatus to:

convert the averaged segments from a time domain signal representation to a frequency domain signal representation as part of processing the data.

14. The apparatus of claim 13, wherein the instructions, when executed by the at least one processor, cause the apparatus to:

extract magnitudes from the frequency domain signal representation at frequencies representing integer multiples of a speed of the drive shaft as part of processing the data.

15. The apparatus of claim 14, wherein the instructions, when executed by the at least one processor, cause the apparatus to:

compare the magnitudes to thresholds established for a healthy drive shaft; and

schedule at least one of an inspection and a maintenance activity when the comparison indicates that the drive shaft is unhealthy.

16. An aircraft comprising:

a drive shaft comprising a plurality of components;

a plurality of sensors configured to measure vibration associated with the aircraft;

a control computer configured to;

sample measurements from the sensors to obtain data;

process the data to obtain a qualitative and quantitative assessment of a health of at least one of the components based on an application of the data to at least one model; and

output the assessment.

17. The aircraft of claim 16, wherein the control computer is configured to:

time-stamp the sampled measurements,

wherein the processing of the data is based on a comparison of sampled measurements at different times based on the time-stamps.

18. The aircraft of claim 16, wherein the health of the at least one component pertains to at least one of:

unbalance, misalignment, loss of bolt preload, and coupling cracking.