Alternate-secondary system in pressure control mode for minimal braking disruption in a primary-alternate braking system
A method of controlling an aircraft braking system includes initiating the aircraft braking system by receiving a first brake command at a primary system to actuate braking via the primary system, receiving the first brake command at an alternate system, and in response to the primary system losing an ability to control a brake, controlling the braking of the brake via the alternate system.
1. An aircraft braking system comprising:
a first brake control unit configured to determine a first brake pressure and to operate at the first brake pressure, wherein the first brake control unit comprises a first outboard brake control card (BCC) and a first inboard BCC;
a second brake control unit operatively coupled to the first brake control unit and configured to determine a second brake pressure by subtracting a deltaP from the first brake pressure and to operate at the second brake pressure, wherein the second brake control unit comprises a second outboard BCC and a second inboard BCC, and wherein either the first brake control unit or the second brake control unit is a primary brake control unit and the other of the first brake control unit and the second brake control unit is a secondary brake control unit;
a first hydraulic pressure source;
a first outboard dual brake control valve module fluidly connected to the first hydraulic pressure source and operatively connected to the first outboard BCC;
a first inboard dual brake control valve module fluidly connected to the first hydraulic pressure source and operatively connected to the first inboard BCC; and
a first shuttle valve operatively coupled to the first and second brake control units and having a check ball, the first shuttle valve configured to receive the first brake pressure and the second brake pressure, wherein the check ball is forced to one side of the first shuttle valve in response to a pressure change such that the first shuttle valve switches operation from the primary brake control unit to the secondary brake control unit, wherein the deltaP is a predetermined pressure difference that would cause the check ball of the first shuttle valve to switch position in response to the first brake control unit ceasing to provide the first brake pressure.
2. The aircraft braking system of claim 1 , wherein the first brake pressure is determined relative to a pedal displacement.
3. The aircraft braking system of claim 2 , wherein a first pedal position sensor is operatively interconnected with the first inboard BCC of the first brake control unit, wherein the first pedal position sensor is configured to determine the pedal displacement.
4. The aircraft braking system of claim 1 , further comprising:
a second hydraulic pressure source;
a second outboard dual brake control valve module fluidly connected to the second hydraulic pressure source and operatively connected to the second outboard BCC; and
a second inboard dual brake control valve module fluidly connected to the second hydraulic pressure source and operatively connected to the second inboard BCC.
5. The aircraft braking system of claim 4 , further comprising a second shuttle valve operatively coupled to the first and second brake control units, the second shuttle valve configured to receive the first brake pressure.
6. The aircraft braking system of claim 5 , wherein the first shuttle valve is fluidly connected to a first outboard brake, the first outboard dual brake control valve module, and the second outboard dual brake control valve module, and wherein the second shuttle valve is fluidly connected to a first inboard brake, the first inboard dual brake control valve module, and the second inboard dual brake control valve module.