System and Method for Aircraft Braking System Usage Monitoring

• US 20080275599A1
• Filed: 07/21/2008
• Published: 11/06/2008
• Est. Priority Date: 12/04/2001
• Status: Abandoned Application

• Current Assignee: Hydro-Aire, Inc. (Crane Company)
• Original Assignee: Hydro-Aire, Inc. (Crane Company)
• Inventors: DeVlieg, Garrett H.
• Application Number:
  US12/176,969
• Publication Number:
  US 20080275599A1
• Time in Patent Office: Days
• US Class Current: 701/16
• CPC Class Codes: B60T 17/22 Devices for monitoring or checking brake systems; Signal devices
• CPC Class Codes: B60T 2270/406 Test-mode; Self-diagnosis
• CPC Class Codes: B60T 8/1703 for aircrafts
• CPC Class Codes: B60T 8/172 Determining control parameters used in the regulation, e.g. by calculations involving measured or detected parameters B60T8/17551 takes precedence
• CPC Class Codes: B60T 8/325 Systems specially adapted for aircraft
• CPC Class Codes: B60T 8/885 using electrical circuitry
• CPC Class Codes: F16D 66/028 with non-electrical sensors or signal transmission, e.g. magnetic, optical

Abstract

The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance travelled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal.

Claims

1. A system for monitoring wear of a plurality of aircraft parts of an aircraft, comprising:

at least one linear brake wear indicator attached to an aircraft brake, said at least one linear brake wear indicator being configured to move a discrete distance each time the aircraft brake is actuated, said linear brake wear indicator having a plurality of longitudinally arranged markings indicating a distance traveled by the linear brake wear indicator as an indication of brake usage;

at least one corresponding linear position encoder configured to count said plurality of longitudinally arranged markings of said at least one linear brake wear indicator passing by said optical encoder, respectively, to measure the distance traveled by said at least one linear brake wear indicator, respectively, as an indication of brake usage, and said at least one linear position encoder being operative to generate a linear position signal indicating the distance traveled by said at least one linear brake wear indicator, respectively, as an indication of brake usage;

a wheel speed monitor for generating a wheel speed signal indicating wheel speed of the aircraft;

at least one secondary sensor for sensing a parameter of usage of an aircraft part, said at least one secondary sensor being configured to generate a signal indicating a sensed value of said parameter of usage of said aircraft part; and

a control unit configured to determine an estimate of usage of the brake based upon said linear position signal, said control unit being configured to receive said wheel speed signal for distinguishing between static brake applications and moving brake applications based upon said wheel speed signal, said control unit being configured to measure a period of time elapsed during each brake application, and said control unit being configured to determine a distance over which each brake application occurs and to estimate a degree to which each individual brake application contributes to brake wear, based upon the wheel speed during each brake application and said period of time elapsed during each brake application.

2. The system of claim 1, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part comprises an inertial guidance system configured to sense aircraft yaw and to generate a yaw signal indicating aircraft yaw, and wherein said control unit is configured to determine an estimate of usage of a tire based upon said wheel speed signal and said yaw signal.

3. The system of claim 1, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part comprises a meter configured to measure input power to an aircraft standby system and to generate an input power signal;

an aircraft standby system clock configured to measure a period of time elapsed during each usage of the aircraft standby system and to generate a standby system elapsed time signal; and

wherein said control unit is configured to determine an estimate of usage of the aircraft standby system based upon said input power signal and said standby system elapsed time signal.

4. The system of claim 1, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part comprises at least one strain sensor configured to sense load on an aircraft landing gear and to generate a load signal;

a landing gear system clock configured to measure a period of time elapsed during each usage of the landing gear and to generate a landing gear elapsed time signal; and

wherein said control unit is configured to determine an estimate of usage of the aircraft landing gear based upon said load signal and said landing gear elapsed time signal.

5. The system of claim 2, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part further comprises a meter configured to measure input power to an aircraft standby system and to generate an input power signal;

an aircraft standby system clock configured to measure a period of time elapsed during each usage of the aircraft standby system and to generate a standby system elapsed time signal; and

wherein said control unit is configured to determine an estimate of usage of the aircraft standby system based upon said input power signal and said standby system elapsed time signal.

6. The system of claim 2, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part further comprises at least one strain sensor configured to sense load on an aircraft landing gear and to generate a load signal;

a landing gear system clock configured to measure a period of time elapsed during each usage of the landing gear and to generate a landing gear elapsed time signal; and

wherein said control unit is configured to determine an estimate of usage of the aircraft landing gear based upon said load signal and said landing gear elapsed time signal.

7. The system of claim 3, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part further comprises at least one strain sensor configured to sense load on an aircraft landing gear and to generate a load signal;

a landing gear system clock configured to measure a period of time elapsed during each usage of the landing gear and to generate a landing gear elapsed time signal; and

wherein said control unit is configured to determine an estimate of usage of the aircraft landing gear based upon said load signal and said landing gear elapsed time signal.

8. The system of claim 5, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part further comprises at least one strain sensor configured to sense load on an aircraft landing gear and to generate a load signal;

a system clock configured to measure a period of time elapsed during each usage of the landing gear and to generate a landing gear elapsed time signal; and

wherein said control unit is configured to determine an estimate of usage of the aircraft landing gear based upon said load signal and said landing gear elapsed time signal.

9. The system of claim 1, wherein said at least one secondary sensor for sensing a parameter of usage of an aircraft part comprises a temperature sensor configured to sense an aircraft brake temperature and to generate a brake temperature signal indicating brake temperature, and wherein said control unit is configured to receive said brake temperature signal, and wherein said estimate of usage of the brake is based upon said temperature signal.

10. The system of claim 9, wherein said control unit is configured to estimate the degree to which each individual brake application contributes to wear based upon said temperature signal.

11. The system for monitoring wear of an aircraft brake of claim 1, further comprising a memory for storing said estimate of usage of said brake for access of said estimate by ground personnel.

12. The system for monitoring wear of an aircraft brake of claim 1, wherein said control unit comprises a central computer of an anti-skid control system.