AIRCRAFT ELECTRICAL BRAKE CONTROL SYSTEM ARCHITECTURE
First Claim
1. An electric brake system for an aircraft having at least one left landing gear wheel and at least one right landing gear wheel, the system comprising:
- a right brake system control unit configured to generate brake control signals for the at least one right landing gear wheel in response to pilot input;
a left brake system control unit configured to generate brake control signals for the at least one left landing gear wheel in response to pilot input;
at least one right electric brake actuator control coupled to and controlled by the right brake system control unit, the at least one right electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one right landing gear wheel; and
at least one left electric brake actuator control coupled to and controlled by the left brake system control unit, the at least one left electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one left landing gear wheel.
1 Assignment
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Accused Products
Abstract
An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.
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Citations
21 Claims
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1. An electric brake system for an aircraft having at least one left landing gear wheel and at least one right landing gear wheel, the system comprising:
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a right brake system control unit configured to generate brake control signals for the at least one right landing gear wheel in response to pilot input; a left brake system control unit configured to generate brake control signals for the at least one left landing gear wheel in response to pilot input; at least one right electric brake actuator control coupled to and controlled by the right brake system control unit, the at least one right electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one right landing gear wheel; and at least one left electric brake actuator control coupled to and controlled by the left brake system control unit, the at least one left electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one left landing gear wheel. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. An electric brake system for an aircraft having at least one left landing gear wheel and at least one right landing gear wheel, the system comprising:
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at least one left remote data concentrator (“
RDC”
) for the at least one left landing gear wheel, the at least one left RDC being configured to collect wheel data for the at least one left landing gear wheel;at least one right RDC for the at least one right landing gear wheel, the at least one right RDC being configured to collect wheel data for the at least one right landing gear wheel; at least one left electric brake actuator control configured to generate brake control signals for the at least one left landing gear wheel in response to wheel data collected by the at least one left RDC; and at least one right electric brake actuator control configured to generate brake control signals for the at least one right landing gear wheel in response to wheel data collected by the at least one right RDC. - View Dependent Claims (13, 14, 15, 16, 17)
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18. An electric brake system for an aircraft having at least one landing gear wheel, the system comprising:
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a brake system control unit configured to generate brake control signals for at least one landing gear wheel in response to pilot input; and at least one electric brake actuator control coupled to and controlled by the brake system control unit, the at least one electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one landing gear wheel. - View Dependent Claims (19, 20, 21)
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Specification