Method of increasing the service life of aircraft carbon disk brakes

• US 4,923,056 A
• Filed: 02/21/1989
• Issued: 05/08/1990
• Est. Priority Date: 02/21/1989
• Status: Expired due to Term

• Current Assignee: Aircraft Braking Systems Corp. (Meggitt-USA, Inc.), Opus Acquisition Corp. (SPX Corporation)
• Original Assignee: Aircraft Braking Systems Corp. (Meggitt-USA, Inc.)
• Inventors: Nedelk, John
• Primary Examiner(s): Butler, Douglas C.
• Application Number:
  US07/312,994
• Time in Patent Office: 441 Days
• Field of Search: 303/1, 303/9.61, 303/13, 303/2-3, 244/110 A, 244/111, 188/151 A, 188/152, 188/1.11, 188/71.1, 188/71.7, 188/71.8, 188/71.9, 188/79.51, 188/151 R, 188/158, 188/382, 188/196 R, 188/71.5
• US Class Current: 188/71.1
• CPC Class Codes: B60T 13/662 characterised by specified functions of the control system components
• CPC Class Codes: B60T 17/22 Devices for monitoring or checking brake systems; Signal devices
• CPC Class Codes: B60T 8/325 Systems specially adapted for aircraft
• CPC Class Codes: B64C 25/42 Arrangement or adaptation of brakes

Abstract

The invention is directed to a method of increasing and/or extending the operational service life of an aircraft brake disk stack by selectively limiting the number of brake assemblies which comprise the aircraft landing gear configuration and which are put into operation during the time the aircraft is on the ground and subject to taxi-snub braking cycles while also providing that all of the brake assemblies of the total available on the aircraft are operational during landing of the aircraft.

Claims

1. A method of increasing the service life of carbon disks which form the functional braking elements of a brake disk stack of an aircraft brake assembly, each brake assembly associated with a respective wheel of a plurality of wheels which comprise a landing gear configuration of the aircraft, the method comprising the steps of:

establishing a preselected first group of brake assemblies of a total number of brake assemblies which are actuated for both low-pressure and high-pressure braking of the aircraft;

establishing a preselected second group of brake assemblies which comprises the remaining number of the total number of brake assemblies which are actuated only during high-pressure braking of the aircraft;

actuating the first group of brake assemblies during the taxi-snub stops of the aircraft when it is on the ground; and

actuating the first and second groups of brake assemblies during landing of the aircraft.

2. The method of claim 1 wherein the preselection of the second group is accomplished by placing check valves in the brake circuitry of the group, the check valves being set at a preselected threshold pressure above which the brake assemblies of the group are actuated for braking effort.

3. A method of increasing the service life of carbon disks which form the functional braking elements of a brake disk stack of an aircraft brake assembly, each brake assembly associated with a respective wheel PG,12 of a plurality of wheels comprising a landing gear configuration of the aircraft, the method comprising the steps of:

providing a programmable brake controller which operates in conjunction with a pilot'"'"'s control for braking of the aircraft;

installing switch means within the circuitry of each brake assembly, the switch means being interconnected through the brake controller to actuate each of said respective brake assemblies; and

programming the brake controller to select various of the brake assemblies for braking action in accordance with a particular sequence such that all of the brake assemblies are actuated during an aircraft landing operation and only a preselected group of the total of brake assemblies is actuated during taxi braking operations of the aircraft when it is on the ground.

4. The method as set forth in claim 3 wherein an aircraft landing gear comprises an eight-wheel configuration and the controller is programmed to select a first four-wheel group for an initial taxi braking of the aircraft and a second four-wheel group for a subsequent taxi braking, the first and second four-wheel groups being alternated between additional taxi braking of the aircraft, said controller being programmed to revert to an eight-wheel braking of the aircraft when subject to a landing operation.

5. The method as set forth in claim 4 wherein the first four-wheel group selected for initial taxi braking comprises a forward four wheels of the eight-wheel configuration and the second four-wheel group comprises a rearward four wheels of the eight.

6. The method as set forth in claim 4 wherein the first four-wheel group selected for initial taxi braking comprises two forward wheels of the eight-wheel configuration and two rearward wheels of the eight and the second four-wheel group comprises the remaining two forward wheels and the remaining two rearward wheels of the eight-wheel configuration.

7. The method as set forth in claim 4 wherein the first four-wheel group selected for initial taxi braking comprises two outboard forward wheels of the eight-wheel configuration and two outboard rearward wheels of the eight and the second four-wheel group comprises two inboard forward wheels and two inboard rearward wheels of the eight-wheel configuration.

8. The method as set forth in claim 4 wherein the first four-wheel group selected for initial taxi braking comprises two inboard forward wheels and two outboard rearward wheels of the eight-wheel configuration and the second four-wheel group comprises two outboard forward wheels and two inboard rearward wheels of the eight-wheel configuration.

9. The method as set forth in claim 3 wherein the first group of wheels selected for initial taxi braking comprises two wheels of the eight-wheel configuration and each subsequent group comprises a different two of the eight-wheel configuration until all pair combinations of the eight are utilized for taxi braking and the controller repeats the cycle for subsequent taxi braking.

10. The method as set forth in claim 3 wherein the aircraft total wheel and brake assembly comprising the landing gear is a four-wheel configuration and two wheels of the four ar programmed for initial taxi braking and these alternate with the remaining two wheels for subsequent taxi braking, all wheels of the four utilized for braking in a landing situation.

11. The method as set forth in claim 3 wherein an aircraft landing gear comprises a sixteen-wheel configuration and the controller is programmed to select a first group for an initial taxi braking of the aircraft and sequentially selects additional groups for subsequent taxi braking, said controller being programmed to revert to sixteen-wheel braking when subject to a landing operation.