SYSTEMS AND METHODS FOR MONITORING HEALTH OF VIBRATION DAMPING COMPONENTS

• US 20150367963A1
• Filed: 12/06/2011
• Published: 12/24/2015
• Est. Priority Date: 12/06/2011
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: Bradley J. Mitchell, Dane Joe Grgas, David A. Followell, Jeanne C. Maggiore, Kevin L. Swearingen, Stephen Gregory Dame
• Inventors: Swearingen, Kevin L., Mitchell, Bradley J., Maggiore, Jeanne C., Followell, David A., Dame, Stephen Gregory, Grgas, Dane Joe
• Granted Patent: US 9,342,481 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 25/505 Shimmy damping
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: G01M 17/04 Suspension or damping
• CPC Class Codes: G06F 17/00 Digital computing or data processing equipment or methods, specially adapted for specific functions information retrieval, database structures or file system structures therefor G06F16/00
• CPC Class Codes: G07C 5/008 communicating information to a remotely located station transmission systems for measured values G08C

Abstract

A method for health monitoring of a damper associated with a landing gear is described which includes receiving sensor data from a pressure transducer and an accelerometer and optionally a thermal sensor operably mounted on or near the damper, a computer system, and applying, using the computer system, a diagnostic algorithm to the sensor data to induce and predict the health of the damper.

Claims

1. A method for health monitoring of a damper associated with a landing gear comprising:

receiving sensor data from a pressure transducer, a thermal sensor and an accelerometer operably mounted on or near the landing gear, the sensor data including vibration data measured during at least one of takeoff rollout, landing rollout, and ground operations by the accelerometer and a pressure and a temperature of the damper, wherein the damper mechanically links a lower landing gear assembly to an upper landing gear assembly and is configured to reduce a rotational oscillation of the lower landing gear assembly with respect to the upper landing gear assembly; and

applying, with a computer system, a diagnostic algorithm to the sensor data to produce a health assessment of the damper.

2. The method according to claim 21 wherein receiving sensor data at the computer system comprises:

receiving the sensor data at a processor module associated with the pressure transducer, thermal sensor and the accelerometer; and

transmitting the sensor data from the processor module to a data concentrator.

3. The method according to claim 2 wherein applying a diagnostic algorithm to the sensor data comprises evaluating the health of the damper using a health algorithm running on the data concentrator and/or running on a separate computing system, either part of the aircraft or separate.

4. The method according to claim 3 wherein further comprising transmitting the health assessment and the sensor data to a ground-based health application for storage in a database.

5. The method according to claim 4 further comprising operating the ground-based health application to perform trending and identify predicted health of the damper.

6. The method according to claim 2 further comprising collating the sensor data with a plurality of aircraft parameters received by the data concentrator.

7. The method according to claim 2 further comprising filtering, synchronizing and time stamping the sensor data with the processor module before transmitting to the data concentrator.

8. The method according to claim 2 wherein transmitting the sensor data from the processor module to the computer system comprises transmitting the sensor data from a plurality of processor modules, one per damper, to the data concentrator.

9. The method according to claim 21 further comprising:

receiving temperature data from a device operably mounted on the damper; and

including the temperature data as a portion of the sensor data.

10. The method according to claim 21 further comprising:

providing the health assessment to a health application running on an external computer system not aboard the aircraft;

extracting, by the external computer system, relevant historical data from a database; and

determining, with the external computer system, a projected health for the damper using a prognostic algorithm that receives the relevant historical data and health evaluation as inputs.

21. The method according to claim 1 further comprising determining a source of vibration of the landing gear of an aircraft.

11. A health monitoring system for a damper comprising:

a pressure transducer operably mounted to the damper to output pressure data, wherein the damper mechanically links a lower landing gear assembly to an upper landing gear assembly and is configured to reduce a rotational oscillation of the lower landing gear assembly with respect to the upper landing gear assembly;

an accelerometer operably mounted to the landing gear to output vibration data measured during at least one of takeoff rollout, landing rollout, and ground operations; and

a processor module proximate the damper to which said pressure transducer and said accelerometer are communicatively coupled, said processor module programmed to collect sensor data comprising the pressure data and the vibration data and package the sensor data for transmission to an external device; and

a data concentrator communicatively coupled to said processor module and configured to receive the packaged sensor data and to produce a health assessment of the damper based on the packaged sensor data.

13. The health monitoring system according to claim 11 wherein said data concentrator is programmed to evaluate health of the damper using an health algorithm running thereon.

14. The health monitoring system according to claim 13 wherein said data concentrator is programmed to transmit the health evaluation and the sensor data to a ground-based health application for storage in a database.

15. The health monitoring system according to claim 11 wherein said data concentrator is programmed to collate the sensor data with a plurality of aircraft parameters received by said data concentrator.

16. The health monitoring system according to claim 11 wherein said processor module is programmed to filter, synchronize and time stamp the sensor data.

17. The health monitoring system according to claim 11 further comprising a temperature sensor operably mounted to the damper or landing gear to output temperature data, the temperature data included in the sensor data.

18. The health monitoring system according to claim 11 further comprising a ground station communicatively coupled to said data concentrator, said ground station programmed to:

receive a health evaluation from said data concentrator;

extract relevant historical data from a database; and

determine a projected health for the damper using a prognostic algorithm running thereon, the prognostic algorithm receiving the relevant historical data and the health evaluation as inputs.

19. The health monitoring system according to claim 11 further comprising at least one energy harvesting device operable to utilize vibrations of landing gear components to generate power to operate one or more of said pressure transducer, said accelerometer, and said processor module.

12. (canceled)

20. An apparatus for damper health monitoring, said apparatus comprising:

one or more distributed oscillation measurement transducers capable of measuring response attributes of one or more vibration damping components during at least one of takeoff rollout, landing rollout, and ground operations, wherein at least one of the one or more vibration damping components mechanically links a lower landing gear assembly to an upper landing gear assembly and is configured to reduce a rotational oscillation of the lower landing gear assembly with respect to the upper landing gear assembly; and

at least one processor capable of receiving and analyzing data extracted from said one or more distributed oscillation measurement transducers to determine a real-time health, predict future health state, and establish current performance capability of the one or more vibration damping components, and to determine a source of vibration of an aircraft.