AIRCRAFT ELECTRIC BRAKE ACTUATION SYSTEM AND METHOD
First Claim
Patent Images
1. A method comprising:
- determining an aircraft operational state;
measuring an application force supplied to a brake pedal of an aircraft; and
moving an actuator brake to engage an electric brake actuator and de-energizing the electric brake actuator when (i) the determined aircraft operational state is a ground-idle state, wherein the ground-idle state is a state in which the aircraft is moving, and (ii) the measured application force is greater than a set force magnitude.
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Abstract
A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized.
11 Citations
21 Claims
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1. A method comprising:
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determining an aircraft operational state; measuring an application force supplied to a brake pedal of an aircraft; and moving an actuator brake to engage an electric brake actuator and de-energizing the electric brake actuator when (i) the determined aircraft operational state is a ground-idle state, wherein the ground-idle state is a state in which the aircraft is moving, and (ii) the measured application force is greater than a set force magnitude. - View Dependent Claims (2, 3, 4, 5, 20)
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6. An electric brake control system for an aircraft, the electric brake control system comprising:
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an electric brake actuator configured to be controllably energized and, upon being controllably energized, to move to a brake position; an actuator brake configured to move between an engage position, in which the actuator brake prevents movement of the electric brake actuator, and a disengage position, in which the actuator brake does not prevent movement of the electric brake actuator; and a control circuit configured to receive one or more signals representative of aircraft operational state and one or more signals representative of a brake pedal application force, the control circuit being configured to, in response the one or more signals representative of aircraft operational state and the one or more signals representative of a brake pedal application force, command the actuator brake to the engage position and to de-energize the electric brake actuator when the aircraft operational state is a ground-idle state and the application force is greater than a set force magnitude, wherein the ground-idle state is a state in which the aircraft is moving. - View Dependent Claims (7, 8, 9, 10, 11, 21)
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12. An electric brake control system for an aircraft, the electric brake control system comprising:
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a plurality of electric brake actuators, each electric brake actuator of the plurality of electric brake actuators being configured to be controllably energized and, upon being controllably energized, to move to a brake position; a plurality of actuator brakes, each actuator brake of the plurality of actuator brakes being configured to move between an engage position, in which the actuator brake prevents movement of an electric brake actuator of the plurality of electric brake actuators, and a disengage position, in which the actuator brake does not prevent movement of the electric brake actuator; and a control circuit coupled to receive one or more signals representative of a brake pedal application force and one or more signals representative of an aircraft operational state, the control circuit being configured to, in response to the one or more signals representative of the brake pedal application force and the one or more signals representative of the aircraft operational state; (i) determine the aircraft operational state, (ii) determine the brake pedal application force supplied to the brake pedals, and (iii) command the plurality of actuator brakes to the engage position and de-energize the electric brake actuators when that the aircraft operational state is a ground-idle state and the brake pedal application force is greater than a set force magnitude, wherein the ground-idle state is a state in which the aircraft is moving at less than a predetermined speed. - View Dependent Claims (13, 14, 15, 16, 17, 18)
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19. (canceled)
Specification