Brake system for aircraft
AssigneeTextron Innovations Inc.
InventorsDarrin Michael Jones, Michael Troy Heeren, Dennis Stephen Bradfield
Life of this patent
Estimating the term…
Abstract
Disclosed is a brake system for aircraft that uses a control unit that is configured to control actuators at each wheel using one channel operating an associated brake control module, and other actuators at the same wheel using a second module operated completely independently using a second module. The use of the first and second groups of actuators are alternated periodically, e.g., for each flight.
Claims14
A brake system for aircraft comprising:
- a control unit having a first channel of communications controlling a first brake system existing at a wheel, and a second channel of communications controlling a second brake system existing at the wheel, the first brake system includes a first group of pistons existing at a set of first clocked positions about the wheel, and the second system includes a second group of pistons existing at a set of second clocked positions about the wheel;
- the control unit operable in a first mode wherein:
- (i) the first channel of communications actively controls and operates the first group of pistons to selectively and substantially uniformly apply brake pressure at each of the first clocked positions to the wheel, and, (ii) the second channel of communications and the second brake system are placed on stand-by and not operated during the first mode unless a failure occurs in the first channel;
- the control unit, after the completion of an event related to a first flight durational component, and for a second flight durational component, implements a second mode which:
- (i) causes the second channel of communications to become active and control the second group of pistons in selectively and uniformly apply brake pressure at each of the second clocked positions to the wheel , and (ii) places the first channel of communications and the first brake system into standby mode, such that the first brake system is not operated unless a failure occurs in the second channel.
A brake system comprising:
- a brake control unit;
- the brake control unit adapted to receive pilot input signals and administering braking commands via a first channel to a first brake control module, the first brake control module, upon receiving the first-flight-event braking commands, controlling braking forces to a first set of actuators, the first set of actuators being substantially equally spaced apart onto a wheel brake during a first portion of a flight schedule;
- and
- the brake control unit, after the first portion, being configured to switch to a second channel, the second channel administering braking commands to a second brake system using a second brake control module, the second brake control module causing a second set of actuators to apply varying degrees of braking forces onto the wheel brake during or about the time of a second portion of a flight schedule, the second set of actuators being substantially equally spaced apart and intermittently located within each of the actuators in the first set of actuators.
A process for operating a brake system on an aircraft, the aircraft having a plurality of wheels, a brake control unit which is configured to receive braking commands from at least one pilot, and a plurality of actuators at each wheel brake in said plurality, the process comprising:
- controlling a first group of actuators at each wheel brake using a first brake control module operating according to signals transmitted by a first channel of the control unit, the first group of actuators being clocked about the brake at substantially equally spaced apart angular locations;
- controlling a second group of actuators at each wheel using signals transmitted by a second channel of said control unit, the second group being clocked about the brake at substantially equally spaced apart angular locations different from the locations of the first group;
- periodically alternating between the use of the first group of actuators and the second group of actuators according to a degradation disparity prevention routine, the alternating occurring according to a defined flight event term, and;
- a routine interruption process, the routine interruption process detecting a failure in whichever of the first and second group of actuators is currently operating, interrupting the routine, and operating the other group.
Dependencies are inferred from the claim text.