System and method for aircraft braking system usage monitoring

• US 20050269873A1
• Filed: 05/11/2005
• Published: 12/08/2005
• Est. Priority Date: 12/04/2001
• Status: Active Grant

• Current Assignee: Hydro-Aire Aerospace Corporation (Crane Company)
• Original Assignee: Hydro-Aire, Inc. (Crane Company)
• Inventors: DeVlieg, Garrett H.
• Granted Patent: US 7,484,599 B2
• Time in Patent Office: Days
• US Class Current: 303/122.30
• 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

1-43. -43. (canceled)

44. A system for monitoring wear of an aircraft part, comprising:

at least one sensor for sensing a parameter of usage of an aircraft part and for generating a signal indicating a sensed value of said parameter of usage of said aircraft part;

means for measuring a period of time elapsed during each usage of said aircraft part and generating an elapsed time signal; and

means for determining an estimate of usage of said part based upon said elapsed time signal and said signal indicating said sensed value of said parameter of usage of said aircraft part.

45. The system for monitoring wear of an aircraft part of claim 44, wherein said aircraft part is a brake, and said at least one sensor for sensing a parameter of usage of an aircraft part and for generating a signal indicating a sensed value of said parameter of usage of said aircraft part comprises:

a linear brake wear indicator attached to the brake, wherein each time the brake is actuated, the linear brake wear indicator moves a discrete distance; and

a linear position encoder for measuring and generating a linear position signal indicating the distance traveled by the linear brake wear indicator as an indication of brake usage, and wherein said means for determining an estimate of usage determines an estimate of usage of said brake based upon said linear position signal.

46. The system for monitoring wear of an aircraft part of claim 45, wherein said linear brake wear indicator includes a plurality of longitudinally arranged markings, and said linear position encoder comprises an optical encoder for counting said markings passing by said optical encoder for determining the distance traveled by the linear brake wear indicator upon brake actuation, for indicating the distance traveled by the linear brake wear indicator as an indication of brake usage.

47. The system for monitoring wear of an aircraft part of claim 45, wherein said linear brake wear indicator comprises a brake wear pin.

48. The system for monitoring wear of an aircraft part of claim 45, wherein said linear brake wear indicator includes a plurality of longitudinally arranged digitized markings indicating longitudinal position on said linear brake wear indicator, and said linear position encoder comprises an optical encoder for encoding the digitized markings, for indicating the distance traveled by the linear brake wear indicator as an indication of brake usage.

49. The system for monitoring wear of an aircraft part of claim 45, further comprising a wheel speed monitor for generating a wheel speed signal indicating wheel speed of the aircraft, and said means for determining an estimate of usage receives said wheel speed signal for distinguishing between static brake applications and moving brake applications based upon said wheel speed signal.

50. The system for monitoring wear of an aircraft part of claim 49, wherein said wheel speed monitor comprises a wheel speed sensor.

51. The system for monitoring wear of an aircraft part of claim 49, wherein said wheel speed monitor comprises an aircraft speed sensor.

52. The system for monitoring wear of an aircraft part of claim 49, wherein said means for determining an estimate of usage further comprises means for determining the distance over which each brake application occurs, based upon the wheel speed during each brake application and said period of time elapsed during each brake application, for determining the degree to which each individual brake application contributes to brake wear.

53. The system for monitoring wear of an aircraft part of claim 45, further comprising means for sensing brake temperature, and for generating a temperature signal indicating brake temperature that is received by said means for determining an estimate of usage, and wherein said estimate of usage is based upon said temperature signal.

54. The system for monitoring wear of an aircraft part of claim 53, wherein said means for determining an estimate of usage further comprises means for estimating the degree to which each individual brake application contributes to wear based upon said temperature signal.

55. The system for monitoring wear of an aircraft part of claim 44, wherein said aircraft part is a standby system, and said at least one sensor for sensing a parameter of usage of an aircraft part and for generating a signal indicating a sensed value of said parameter of usage of said aircraft part comprises:

means for sensing input power to said standby system and for generating an input power signal received by said means for means for determining an estimate of usage.

56. The system for monitoring wear of an aircraft part of claim 44, wherein said aircraft part is a landing gear, and said at least one sensor for sensing a parameter of usage of an aircraft part and for generating a signal indicating a sensed value of said parameter of usage of said aircraft part comprises:

means for sensing load on said landing gear and for generating a load signal received by said means for means for determining an estimate of usage.

57. The system for monitoring wear of an aircraft part of claim 44, further comprising means for storing said estimate of usage of said brake for access of said estimate by ground personnel.

58. The system for monitoring wear of an aircraft part of claim 44, wherein said at least one sensor for sensing a parameter comprises a plurality of sensors for sensing usage of a plurality of brakes of the aircraft, and said means for determining an estimate of usage comprises a central computer.

59. A method for monitoring wear of an aircraft part, comprising:

sensing at least one parameter of usage of an aircraft part and generating a signal indicating a sensed value of said at least one parameter of usage of said aircraft part;

measuring a period of time elapsed during each usage of said aircraft part and generating an elapsed time signal; and

determining an estimate of usage of said aircraft part based upon said elapsed time signal and said signal indicating said sensed value of said parameter of usage of said aircraft part.

60. The method for monitoring wear of an aircraft part of claim 59, wherein said aircraft part is a brake, and said step of sensing a parameter of usage of at least one aircraft part and generating a signal indicating a sensed value of said at least one parameter of usage of said aircraft part comprises:

providing a linear brake wear indicator attached to the brake, wherein each time the brake is actuated, the linear brake wear indicator moves a discrete distance; and

measuring the linear position of said linear brake wear indicator and generating a linear position signal indicating the distance traveled by the linear brake wear indicator as an indication of brake usage, and wherein said step of determining an estimate of usage comprises determining an estimate of usage of said brake based upon said linear position signal.

61. The method for monitoring wear of an aircraft part of claim 60, wherein said linear brake wear indicator includes a plurality of longitudinally arranged markings, and said steps of measuring the linear position of said linear brake wear indicator and generating a linear position signal comprise providing an optical encoder for counting said markings passing by said optical encoder for determining the distance traveled by the linear brake wear indicator upon brake actuation, for indicating the distance traveled by the linear brake wear indicator as an indication of brake usage.

62. The method for monitoring wear of an aircraft part of claim 60, wherein said linear brake wear indicator includes a plurality of longitudinally arranged digitized markings indicating longitudinal position on said linear brake wear indicator, and said steps of measuring the linear position of said linear brake wear indicator and generating a linear position signal comprise providing an optical encoder for encoding the digitized markings, for indicating the distance traveled by the linear brake wear indicator as an indication of brake usage.

63. The method for monitoring wear of an aircraft part of claim 60, further comprising the step of generating a wheel speed signal indicating wheel speed of the aircraft, and said step of determining an estimate of usage comprises distinguishing between static brake applications and moving brake applications based upon said wheel speed signal.

64. The method for monitoring wear of an aircraft part of claim 63, wherein said step of generating a wheel speed signal comprises providing a wheel speed sensor for indicating wheel speed of the aircraft.

65. The method for monitoring wear of an aircraft part of claim 63, wherein said step of generating a wheel speed signal comprises determining wheel speed based upon speed of the aircraft speed.

66. The method for monitoring wear of an aircraft part of claim 63, wherein said step of determining an estimate of usage further comprises determining the distance over which each brake application occurs, based upon the wheel speed during each brake application and said period of time elapsed during each brake application, to determine the degree to which each individual brake application contributes to brake wear.

67. The method for monitoring wear of an aircraft part of claim 60, further comprising sensing brake temperature, and generating a temperature signal indicating brake temperature, and wherein said estimate of usage is based upon said temperature signal.

68. The method for monitoring wear of an aircraft part of claim 67, wherein said step of determining an estimate of usage further comprises estimating the degree to which each individual brake application contributes to wear based upon said temperature signal.

69. The method for monitoring wear of an aircraft part of claim 59, wherein said aircraft part is a standby system, and said step of sensing at least one parameter of usage of at least one aircraft part and generating a signal indicating a sensed value of said at least one parameter of usage of said aircraft part comprises:

sensing input power to said standby system and generating an input power signal.

70. The method for monitoring wear of an aircraft part of claim 59, wherein said aircraft part is a landing gear, and said step of sensing at least one parameter of usage of at least one aircraft part and generating a signal indicating a sensed value of said at least one parameter of usage of said aircraft part comprises:

sensing load on said landing gear and generating a load signal.

71. The method for monitoring wear of an aircraft part of claim 59, further comprising the step of storing said estimate of usage of said aircraft part for access of said estimate by ground personnel.