Non-contact infrared temperature sensor for health monitoring of rotorcraft bearings

• US 10,222,297 B2
• Filed: 10/05/2016
• Issued: 03/05/2019
• Est. Priority Date: 10/05/2016
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Burnett, Michael Christopher, Cravener, Kyle Thomas
• Primary Examiner(s): LaBalle, Clayton E.
• Assistant Examiner(s): Rhodes, Jr., Leon W
• Application Number:
  US15/285,569
• Publication Number:
  US 20180095005A1
• Time in Patent Office: 881 Days
• Field of Search: None
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: F16C 2233/00 Monitoring condition, e.g. temperature, load, vibration
• CPC Class Codes: F16C 2326/43 Aeroplanes; Helicopters
• CPC Class Codes: F16C 27/02 Sliding-contact bearings
• CPC Class Codes: F16C 41/00 Other accessories, e.g. devices integrated in the bearing not relating to the bearing function as such
• CPC Class Codes: G01J 5/0022 for sensing the radiation of moving bodies
• CPC Class Codes: G01M 13/04 Bearings

Abstract

The present invention includes an apparatus and method for measuring hysteretic heating or stress of one or more bearings of a craft comprising: one or more non-contact temperature sensors attached to the craft and directed toward the one or more bearings; and a computer connected to the one or more non-contact temperature sensors that measure the temperature, the stress, or both of the one or more bearings before, during, or after operation of the craft, wherein the one or more non-contact temperature sensors measure a change in temperature in the one or more bearings to monitor for heating or stress of the bearings.

Claims

1. A method for measuring a temperature of one or more bearings associated with a rotor assembly of a craft comprising:

attaching one or more non-contact temperature sensors on the craft to measure a change in temperature in the one or more bearings; and

connecting the one or more non-contact temperature sensors to a computer;

receiving a temperature signal from the one or more non-contact temperature sensors; and

monitoring the temperature, stress, or both, of the one or more bearings in real-time before, during, or after craft operations using the computer and the one or more non-contact temperature sensors.

2. The method of claim 1, wherein the one or more non-contact temperature sensors are an infrared heat sensor or a laser heat sensor.

3. The method of claim 1, further comprising providing a pilot with real-time temperature information and warnings to limit craft performance.

4. The method of claim 1, wherein the computer is a flight control computer of an aircraft.

5. The method of claim 1, wherein one or more bearings are selected from a centrifugal force bearing, a hub spring bearing, a laminated rubber bearing, an elastomeric flapping bearing, an elastomeric pitch change bearing, a metal bearing, a composite bearing, a pitch link rod end bearing, a swashplate bearing, a spherical pitch change bearing, or a control system bearings.

6. The method of claim 1, wherein the computer monitors and displays temperature information in a cockpit of the craft.

7. The method of claim 1, wherein the one or more non-contact temperature sensors comprise two or more non-contact temperature sensors directed at different portions of the same bearing.

8. The method of claim 1, wherein the one or more non-contact temperature sensors are movable to measure the temperature of various portions of the same elastomeric bearing or measure the temperature of more than one bearing.

9. The method of claim 1, wherein the craft is an aircraft, and the aircraft is a fixed-wing aircraft, a helicopter, or a vertical take off and landing rotorcraft.

10. The method of claim 1, wherein the one or more non-contact temperature sensors provide a sweep of temperature ranges across a surface of the one or more bearings.

11. The method of claim 1, wherein the one or more bearings are elastomeric or silicone bearings.

12. The method of claim 1, wherein the non-contact temperature sensors are wireless, permanent or removable.

13. The method of claim 1, wherein the change in temperature is heating or cooling.

14. An apparatus that measures heating, cooling, or stress of one or more bearings associated with a rotor assembly of an aircraft comprising:

one or more non-contact temperature sensors attached to the aircraft and directed toward the one or more bearings; and

a computer connected to the one or more non-contact temperature sensors that measure the temperature, the stress, or both of the one or more bearings in real-time before, during, or after operation of the aircraft, wherein the one or more non-contact temperature sensors measure a change in temperature in the one or more bearings to monitor for heating or stress of the bearings in real-time before, during, or after operation of the aircraft.

15. The apparatus of claim 14, wherein the one or more non-contact temperature sensors are an infrared heat sensor or a laser heat sensor.

16. The apparatus of claim 14, wherein the apparatus further comprises a display that provides a pilot with real-time temperature information and warnings to limit aircraft performance.

17. The apparatus of claim 14, wherein the computer is a flight control computer of the aircraft.

18. The apparatus of claim 14, wherein the one or more bearings are selected from a centrifugal force bearing, a hub spring bearing, a laminated rubber bearing, an elastomeric flapping bearing, an elastomeric pitch change bearing, a metal bearing, a composite bearing, a pitch link rod end bearing, a swashplate bearing, a spherical pitch change bearing, or a control system bearings.

19. The apparatus of claim 14, wherein the computer monitors and displays temperature and rotor performance information in a cockpit of the aircraft.

20. The apparatus of claim 14, wherein the one or more non-contact temperature sensors comprise two or more non-contact temperature sensors are directed at different portions of the same bearing.

21. The apparatus of claim 14, wherein the one or more non-contact temperature sensors can be moved to measure the temperature of various portions of the same elastomeric bearing or measure the temperature of more than one bearing.

22. The apparatus of claim 14, wherein the aircraft is a fixed-wing aircraft, a helicopter, or a vertical take off and landing rotorcraft.

23. The apparatus of claim 14, wherein the one or more non-contact temperature sensors provide a sweep of temperature ranges across a surface of the one or more bearings.

24. The apparatus of claim 14, wherein the one or more bearings are elastomeric or silicone bearings.

25. The apparatus of claim 14, wherein the non-contact temperature sensors are at least one or wireless, permanent or removable.

26. A method for measuring hysteretic heating or cooling of bearings associated with a rotor assembly of an aircraft comprising:

identifying one or more bearings of the aircraft to monitor for heating or stress;

attaching one or more non-contact temperature sensors on the aircraft to measure a change in temperature in the one or more bearings;

connecting the one or more non-contact temperature sensors to a computer;

receiving a temperature signal from the one or more non-contact temperature sensors; and

monitoring the temperature of the one or more bearings in real-time using the computer and displaying the same before, during, or after aircraft operations.

27. The method of claim 26, wherein the non-contact temperature sensors are wireless, permanent or removable.