Integrated hanger bearing monitor

• US 10,262,516 B2
• Filed: 06/01/2017
• Issued: 04/16/2019
• Est. Priority Date: 06/01/2016
• Status: Active Grant

• Current Assignee: GPMS International, Inc
• Original Assignee: Green Power Monitoring Systems LLC
• Inventors: Bechhoefer, Eric Robert
• Primary Examiner(s): Dunn, Alex C
• Application Number:
  US15/610,798
• Publication Number:
  US 20170352239A1
• Time in Patent Office: 684 Days
• CPC Class Codes: B64D 1/08 the articles being load-carrying devices
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: F16C 19/522 related to load on the bearing, e.g. bearings with load sensors or means to protect the bearing against overload
• CPC Class Codes: F16C 19/527 related to vibration and noise
• CPC Class Codes: F16C 2326/43 Aeroplanes; Helicopters in general B64C
• CPC Class Codes: F16C 35/047 with a base plate substantially parallel to the axis of rotation, e.g. horizontally mounted pillow blocks
• CPC Class Codes: G01M 13/045 Acoustic or vibration analysis
• CPC Class Codes: G07C 5/085 using electronic data carriers
• CPC Class Codes: G08B 21/0423 detecting deviation from an expected pattern of behaviour or schedule

Abstract

An integrated hanger bearing monitor is provided for reducing installation time and added weight that includes a sensor and an interconnect on a mounting bracket that is sized and configured to be attached to a hanger bearing mounting bracket via connectors that mount the hanger bearing mounting bracket to the helicopter.

Claims

1. An integrated hanger bearing monitor for a helicopter comprising:

a monitor bracket configured to be mounted to a hanger bearing bracket, the monitor bracket including two apertures, each surrounded by respective recessed areas, wherein the hanger bearing bracket is configured to be attached to a tail boom of the helicopter and is configured to be attached, with two connectors, to a hanger bearing that is configured to support a tail rotor driveshaft of the helicopter and wherein when the monitor bracket is mounted to the hanger bearing bracket the two connectors respectively pass through the two apertures and engage with the respective recessed areas; and

a sensor package including an accelerometer and an interconnect, wherein the sensor package is integrated with the monitor bracket.

2. The integrated hanger bearing monitor of claim 1 further including an enclosure integrated with the monitor bracket, wherein the enclosure contains the sensor package.

3. The integrated hanger bearing monitor of claim 2 wherein the enclosure is fully potted.

4. The integrated hanger bearing monitor of claim 1 wherein the interconnect includes two outputs and wherein the outputs are connected to sensors on the helicopter.

5. The integrated hanger bearing monitor of claim 4 wherein the sensor package includes a first board having a microcontroller, a power supply, and a transceiver, and a second board having the accelerometer, a signal conditioning network, and an analog-to-digital converter.

6. The integrated hanger bearing monitor of claim 5 wherein vibration data measured by the accelerometer is processed in the sensor package and the sensor package sends condition monitoring indicators through the interconnect.

7. The integrated hanger bearing monitor of claim 1 wherein the integrated hanger bearing monitor has a thickness of between 2 cm and 4 cm.

8. The integrated hanger bearing monitor of claim 1 wherein the monitor bracket includes a swale that is sized, shaped, and positioned to prevent the monitor bracket from interfering with the tail rotor driveshaft when the monitor bracket is mounted to the hanger bearing bracket.

9. An integrated hanger bearing monitor for monitoring vibrations associated with a tail rotor shaft assembly of a helicopter, comprising:

a monitor bracket configured to mount to a hanger bearing bracket, the hanger bearing bracket configured to be attached to a tail boom of the helicopter and to couple, with a plurality of connectors, to a hanger bearing configured to support a tail rotor driveshaft of the helicopter, wherein the monitor bracket includes a plurality of apertures, each surrounded by respective recessed areas, and wherein the plurality of connectors respectively pass through the plurality of apertures and engage with the respective recessed areas when the monitor bracket is mounted to the hanger bearing bracket and the hanger bearing is coupled to the hanger bearing bracket; and

a sensor package integrated with the monitor bracket and including a fully potted enclosure, an accelerometer within the enclosure, and an interconnect.

10. The integrated hanger bearing monitor of claim 9 wherein the interconnect includes two outputs and wherein the outputs are connected to sensors on the helicopter.

11. The integrated hanger bearing monitor of claim 9 wherein the sensor package includes a first board having a microcontroller, a power supply, and a transceiver and a second board having the accelerometer, a signal conditioning network, and an analog-to-digital converter.

12. The integrated hanger bearing monitor of claim 10 wherein vibration data measured by the accelerometer is processed in the sensor package and the sensor package sends condition indicators through the interconnect.

13. The integrated hanger bearing monitor of claim 9 wherein the monitor bracket has a thickness of between 2 cm and 4 cm.

14. The integrated hanger bearing monitor of claim 9 wherein the monitor bracket includes a swale that is sized, shaped, and positioned to prevent the monitor bracket from interfering with the tail rotor driveshaft when the monitor bracket is mounted to the hanger bearing bracket.

15. A system for monitoring vibrations associated with a rotor shaft assembly of a helicopter, comprising:

a hanger bearing supporting a tail rotor driveshaft of the helicopter;

a hanger bearing bracket attached to a tail boom of the helicopter, wherein the hanger bearing is attached to the hanger bearing bracket with a plurality of connectors;

a monitor bracket having a plurality of apertures, each aperture being surrounded by respective recessed areas, wherein the monitor bracket is attached to the hanger bearing bracket such that a one of each of the plurality of connectors passes through a one of each of the plurality of apertures and engages with the respective recessed areas, wherein the hanger bearing bracket includes a swale that is sized, shaped, and positioned to prevent the hanger bearing bracket from interfering with the tail rotor driveshaft, and wherein the monitor bracket includes a monitor bracket swale that is sized, shaped, and positioned to approximately match the hanger bearing bracket swale; and

a sensor package attached to the monitor bracket, the sensor package including an accelerometer and an interconnect.

16. The system for monitoring vibrations of claim 15 wherein the interconnect includes two outputs and wherein the outputs are connected to sensors on the helicopter.

17. The system for monitoring vibrations of claim 15 wherein the sensor package includes a first board having a microcontroller, a power supply, and a transceiver and a second board having the accelerometer, a signal conditioning network, and an analog-to-digital converter.

18. The system for monitoring vibrations of claim 15 wherein vibration data measured by the accelerometer is processed in the sensor package and the sensor package sends condition indicators through the interconnect.

19. The system for monitoring vibrations of claim 15 wherein the monitor bracket has a thickness of between 2 cm and 4 cm.