System for reducing carbon brake wear

• US 8,548,652 B2
• Filed: 01/31/2006
• Issued: 10/01/2013
• Est. Priority Date: 01/31/2006
• Status: Active Grant

• Current Assignee: Hydro-Aire Aerospace Corporation (Crane Company)
• Original Assignee: Hydro-Aire Incorporated Subsidiary of Crane Company
• Inventors: DeVlieg, Garrett H., Gowan, John
• Primary Examiner(s): Nguyen, Cuong H
• Application Number:
  US11/343,539
• Publication Number:
  US 20070179686A1
• Time in Patent Office: 2,800 Days
• Field of Search: 701/9, 701/78, 340/438, 340/449, 303/126, 303/191, 303/20, 244/111, 702 33- 34, 188/71.5, 188/71.6, 188/173, 188/246.AA
• US Class Current: 701/9
• CPC Class Codes: B60T 17/18 Safety devices; Monitoring
• CPC Class Codes: B60T 17/221 Procedure or apparatus for checking or keeping in a correct functioning condition of brake systems hydraulic pressure systems in general F15B19/00, F15B21/04; testing structures or apparatus G01M
• CPC Class Codes: B60T 8/00 Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force by changing number of effective brake cylinders in power brake systems B60T17/10

Abstract

A brake monitoring system is described for use on aircraft having carbon brakes. The system displays the number of times the brakes have been applied in a preselected counting interval such as during each takeoff and landing cycle. By raising the pilot'"'"'s awareness of the number of times the brakes have been applied, a more efficient brake use is encouraged in view of the knowledge that carbon brake wear is substantially a function of the number of applications rather than the total energy that is converted thereby. Additionally, the monitoring system provides an indication of the temperature of the brakes which encourages the pilot to maintain a minimum temperature therein beyond which wear is reduced.

Claims

1. A system for enabling a pilot to reduce brake wear on aircraft fitted with a plurality of carbon brakes, comprising:

a switch mechanism for sensing application of said plurality of carbon brakes and for generating a brake application count signal indicating application of said plurality of carbon brakes;

a microprocessor operative to receive said brake application count signal and to tally a cumulative brake application count of the number of times the brakes have been applied during a preselected interval responsive to said count signal, said microprocessor being operative to reduce the cumulative brake application count by one third to one half to generate an adjusted brake application count in the event that the aircraft braking system includes a taxi brake select feature that selectively releases some but not all of said plurality of carbon brakes;

a data retrieval system configured to store said adjusted brake application count; and

a monitor displaying to a pilot in real time a count display of the adjusted brake application count and an indication of a temperature of said brakes, indicating to the pilot to use the brakes less often and with more intensity during taxiing, and to maintain more heat in the brakes while the temperature of said brakes is below a threshold temperature.

2. The system of claim 1, wherein said adjusted brake application count is stored in said data retrieval system and is available for later download.

3. The system of claim 1, wherein said count display changes color when a certain threshold temperature is achieved.

4. The system of claim 3, wherein such threshold temperature is about 350°

F.

5. The system of claim 1, wherein said aircraft has a plurality of brakes and said indication of temperature is based on an average temperature of all of said aircraft'"'"'s brakes.

6. The system of claim 1, wherein said aircraft has a plurality of brakes and said indication of temperature is based on the temperature of the coolest of said aircraft'"'"'s brakes.

7. The system of claim 1, wherein each brake application is sensed mechanically.

8. The system of claim 1, wherein said switch mechanism comprises a microswitch configured to increment said brake application count signal by movement of a brake pedal that is used to actuate the brakes.

9. The system of claim 1, wherein each brake application count is triggered hydraulically.

10. The system of claim 9, wherein a pressure switch is tripped by pressure in a hydraulic system that actuates the brakes.

11. The system of claim 1, wherein said interval comprises one take-off and landing cycle.

12. The system of claim 11, wherein said count resets automatically by engine start.

13. The system of claim 11, wherein said count resets automatically when the aircraft is hooked up to an external power source.