NOSE WHEEL TIRE PRESSURE SENSING SYSTEM AND APPARATUS

• US 20150284108A1
• Filed: 04/07/2014
• Published: 10/08/2015
• Est. Priority Date: 04/07/2014
• Status: Abandoned Application

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: KELLER, STEVEN, SUMMERS, PAUL L.
• Application Number:
  US14/247,060
• Publication Number:
  US 20150284108A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B60C 2200/02 for aircrafts
• CPC Class Codes: B64C 25/36 Arrangements or adaptations of wheels, tyres or axles in general
• 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

Abstract

Landing gear tire pressure sensing systems, methods and apparatuses are provided. In various embodiments, a tire pressure sensing system may be mounting to a landing gear. The system may comprise a rotating portion and a stationary portion. The rotating portion and stationary portion may be in electronic communication. The stationary portion may be configured to communicate an indication of tire pressure to a control unit.

Claims

1. A tire pressure monitoring system, comprising:

a rotating module comprising,

a body configured to be installed in a wheel,

a pressure sensor housed within the body, the pressure sensor in fluid communication with a chamber defined by a tire installed on the wheel; and

a stationary module configured to be mounted on a landing gear of an aircraft comprising a landing gear strut, the stationary module configured to receive data from the rotating module,. wherein the rotating module is configured to be mounted adjacent the landing gear strut, wherein the rotating module is configured to be mounted adjacent the landing gear strut.

2. The tire pressure monitoring system of claim 1, wherein the body comprises a threaded portion and is configured to be installed within a port in the wheel.

3. The tire pressure monitoring system of claim 1, wherein the stationary portion is in electronic communication with a control unit.

4. The tire pressure monitoring system of claim 3, wherein the control unit is configured to provide an indication of tire pressure.

5. The tire pressure monitoring system of claim 4, wherein the indication of tire pressure is at least one of a low pressure indication and a pressure reading.

6. The tire pressure monitoring system of claim 1, wherein the rotating portion further comprises a processor and a memory.

7. The tire pressure monitoring system of claim 1, wherein the body is installed on an in-board potion of the wheel.

8. The tire pressure monitoring system of claim 1, wherein the tire pressure monitoring system is installed on a nose landing gear.

9. The tire pressure monitoring system of claim 8, wherein the nose landing gear is capable of being towed by a tug.

16. The tire pressure monitoring system of claim 1, wherein the wheel is coupled to an axle assembly of the landing gear,

wherein the axle assembly is coupled to the landing gear strut, and

wherein the installation and mounting arrangement of the body and the stationary module allows for towing of the aircraft by the axle.

17. The tire pressure monitoring system of claim 1, wherein the rotating module is configured to be mounted in relatively close proximity to the stationary module.

18. The tire pressure monitoring system of claim 1, wherein the wheel is coupled to the landing gear strut and wherein the rotating module and stationary module are configured to locate in an area between landing gear strut and the wheel.

10. A landing gear, comprising:

a strut comprising a stationary sensor portion mounted to the strut;

an axle operatively coupled to the strut;

a wheel rotatably mounted on the axle and comprising a rotating sensor portion installed in the wheel in electronic communication with the stationary sensor portion; and

a tire mounted on the wheel and defining a chamber that is configured to be pressurized, wherein the rotating sensor portion is in fluid communication with the chamber.

wherein the landing gear is an aircraft landing gear, and

wherein the mounting position of the stationary sensor portion is adjacent to the installation position of the rotating sensor portion.

11. The landing gear of claim 10, wherein the stationary sensor portion is in electronic communication with a control unit.

12. The landing gear of claim 11, wherein the control unit is configured to provide an indication of pressure in the chamber.

13. The landing gear of claim 12, wherein the indication is at least one of a pressure reading and an indicia that the pressure in the chamber is below a threshold.

14. The landing gear of claim 10, wherein the rotating sensor portion comprises a threaded body that is rotatably receivable within a port in the wheel.

15. The landing gear of claim 10, wherein the rotating sensor portion is installed on the in-board side of the wheel, adjacent the strut.

19. The tire pressure monitoring system of claim 10, wherein the rotating sensor portion and the stationary sensor portion are configured to locate in an area between landing gear strut and the wheel.